NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 500,000 Max Cl/Cd: 64.62 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms317-il-500000-n5.txt Download as CSV file: xf-ms317-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY MS(1)-0317 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0147 0.11643 0.11243 -0.0314 1.0000 0.0186
-19.500 -1.0319 0.10935 0.10523 -0.0353 1.0000 0.0187
-19.250 -1.0482 0.10253 0.09828 -0.0390 1.0000 0.0188
-19.000 -1.0634 0.09597 0.09159 -0.0426 1.0000 0.0189
-18.750 -1.0768 0.08985 0.08535 -0.0458 1.0000 0.0190
-18.500 -1.0886 0.08409 0.07946 -0.0488 1.0000 0.0191
-18.250 -1.0982 0.07877 0.07401 -0.0515 1.0000 0.0193
-18.000 -1.1060 0.07388 0.06900 -0.0540 1.0000 0.0194
-17.750 -1.1118 0.06941 0.06442 -0.0561 1.0000 0.0196
-17.500 -1.1157 0.06531 0.06020 -0.0579 1.0000 0.0197
-17.250 -1.1177 0.06160 0.05637 -0.0595 1.0000 0.0199
-17.000 -1.1180 0.05825 0.05291 -0.0608 1.0000 0.0201
-16.750 -1.1185 0.05498 0.04955 -0.0619 1.0000 0.0203
-16.500 -1.1187 0.05185 0.04636 -0.0629 1.0000 0.0205
-16.250 -1.1169 0.04909 0.04353 -0.0636 1.0000 0.0207
-16.000 -1.1132 0.04661 0.04099 -0.0642 1.0000 0.0210
-15.750 -1.1081 0.04438 0.03869 -0.0645 1.0000 0.0212
-15.500 -1.1020 0.04234 0.03659 -0.0647 1.0000 0.0215
-15.250 -1.0954 0.04044 0.03462 -0.0648 1.0000 0.0218
-15.000 -1.0879 0.03864 0.03276 -0.0647 1.0000 0.0221
-14.750 -1.0795 0.03698 0.03103 -0.0646 1.0000 0.0224
-14.500 -1.0704 0.03541 0.02939 -0.0644 1.0000 0.0227
-14.250 -1.0602 0.03397 0.02788 -0.0641 1.0000 0.0230
-14.000 -1.0491 0.03262 0.02646 -0.0638 1.0000 0.0233
-13.750 -1.0391 0.03122 0.02502 -0.0633 1.0000 0.0237
-13.500 -1.0290 0.02987 0.02363 -0.0629 1.0000 0.0240
-13.250 -1.0175 0.02866 0.02241 -0.0623 1.0000 0.0244
-13.000 -1.0049 0.02759 0.02131 -0.0617 1.0000 0.0249
-12.750 -0.9919 0.02661 0.02029 -0.0610 1.0000 0.0254
-12.500 -0.9793 0.02570 0.01934 -0.0601 1.0000 0.0259
-12.250 -0.9574 0.02475 0.01834 -0.0609 0.9878 0.0265
-12.000 -0.9330 0.02385 0.01738 -0.0621 0.9737 0.0271
-11.750 -0.9116 0.02280 0.01630 -0.0628 0.9579 0.0278
-11.500 -0.8917 0.02195 0.01541 -0.0629 0.9421 0.0284
-11.250 -0.8738 0.02119 0.01459 -0.0624 0.9278 0.0291
-11.000 -0.8568 0.02051 0.01383 -0.0615 0.9148 0.0298
-10.750 -0.8407 0.01989 0.01313 -0.0605 0.9024 0.0305
-10.500 -0.8215 0.01925 0.01243 -0.0601 0.8921 0.0313
-10.250 -0.8009 0.01862 0.01175 -0.0599 0.8820 0.0323
-10.000 -0.7785 0.01807 0.01115 -0.0599 0.8737 0.0335
-9.750 -0.7550 0.01757 0.01059 -0.0599 0.8654 0.0348
-9.500 -0.7314 0.01707 0.01004 -0.0599 0.8580 0.0361
-9.250 -0.7069 0.01660 0.00956 -0.0600 0.8507 0.0376
-9.000 -0.6818 0.01620 0.00910 -0.0601 0.8440 0.0393
-8.750 -0.6564 0.01578 0.00866 -0.0602 0.8380 0.0413
-8.500 -0.6302 0.01539 0.00826 -0.0604 0.8321 0.0439
-8.250 -0.6037 0.01502 0.00787 -0.0607 0.8265 0.0469
-8.000 -0.5768 0.01469 0.00751 -0.0609 0.8215 0.0504
-7.750 -0.5495 0.01433 0.00716 -0.0613 0.8168 0.0543
-7.500 -0.5217 0.01400 0.00684 -0.0617 0.8119 0.0588
-7.250 -0.4937 0.01371 0.00654 -0.0621 0.8070 0.0640
-7.000 -0.4656 0.01341 0.00624 -0.0625 0.8023 0.0697
-6.750 -0.4370 0.01312 0.00596 -0.0630 0.7979 0.0755
-6.500 -0.4081 0.01285 0.00570 -0.0635 0.7932 0.0818
-6.250 -0.3791 0.01259 0.00545 -0.0640 0.7886 0.0891
-6.000 -0.3499 0.01232 0.00520 -0.0646 0.7845 0.0972
-5.750 -0.3205 0.01207 0.00496 -0.0652 0.7805 0.1065
-5.500 -0.2907 0.01179 0.00474 -0.0659 0.7763 0.1186
-5.250 -0.2607 0.01151 0.00453 -0.0667 0.7720 0.1339
-4.750 -0.2002 0.01091 0.00411 -0.0683 0.7640 0.1799
-4.500 -0.1694 0.01055 0.00388 -0.0694 0.7603 0.2160
-4.250 -0.1380 0.01015 0.00367 -0.0706 0.7564 0.2582
-4.000 -0.1061 0.00974 0.00345 -0.0719 0.7525 0.3061
-3.750 -0.0734 0.00927 0.00321 -0.0735 0.7489 0.3686
-3.500 -0.0395 0.00871 0.00298 -0.0754 0.7454 0.4538
-3.250 -0.0067 0.00842 0.00289 -0.0768 0.7422 0.5162
-3.000 0.0252 0.00830 0.00289 -0.0777 0.7386 0.5535
-2.750 0.0565 0.00825 0.00292 -0.0784 0.7346 0.5763
-2.500 0.0876 0.00825 0.00294 -0.0789 0.7304 0.5932
-2.250 0.1186 0.00828 0.00295 -0.0795 0.7265 0.6085
-2.000 0.1494 0.00834 0.00300 -0.0800 0.7229 0.6230
-1.750 0.1802 0.00837 0.00305 -0.0805 0.7192 0.6314
-1.500 0.2111 0.00840 0.00309 -0.0811 0.7148 0.6392
-1.250 0.2417 0.00845 0.00311 -0.0815 0.7086 0.6472
-1.000 0.2713 0.00852 0.00315 -0.0816 0.6952 0.6558
-0.750 0.3013 0.00860 0.00312 -0.0819 0.6766 0.6634
-0.500 0.3305 0.00865 0.00314 -0.0820 0.6621 0.6672
-0.250 0.3604 0.00870 0.00315 -0.0824 0.6502 0.6698
0.000 0.3904 0.00876 0.00317 -0.0827 0.6368 0.6724
0.250 0.4201 0.00883 0.00317 -0.0830 0.6207 0.6750
0.500 0.4497 0.00892 0.00318 -0.0833 0.6028 0.6776
0.750 0.4792 0.00904 0.00320 -0.0837 0.5834 0.6801
1.000 0.5085 0.00918 0.00323 -0.0840 0.5609 0.6821
1.250 0.5362 0.00939 0.00331 -0.0839 0.5264 0.6840
1.500 0.5618 0.00980 0.00347 -0.0836 0.4691 0.6860
1.750 0.5860 0.01038 0.00373 -0.0831 0.4034 0.6881
2.000 0.6109 0.01090 0.00400 -0.0828 0.3507 0.6901
2.250 0.6366 0.01134 0.00423 -0.0826 0.3083 0.6921
2.500 0.6626 0.01176 0.00447 -0.0825 0.2734 0.6942
2.750 0.6888 0.01213 0.00469 -0.0824 0.2444 0.6965
3.000 0.7151 0.01249 0.00491 -0.0823 0.2202 0.6987
3.250 0.7416 0.01282 0.00513 -0.0822 0.2002 0.7008
3.500 0.7679 0.01313 0.00535 -0.0820 0.1839 0.7028
3.750 0.7940 0.01341 0.00557 -0.0819 0.1711 0.7045
4.000 0.8202 0.01369 0.00581 -0.0817 0.1606 0.7062
4.250 0.8466 0.01395 0.00604 -0.0815 0.1525 0.7080
4.500 0.8723 0.01425 0.00629 -0.0813 0.1447 0.7099
4.750 0.8985 0.01450 0.00653 -0.0811 0.1387 0.7120
5.000 0.9241 0.01479 0.00679 -0.0808 0.1327 0.7142
5.250 0.9496 0.01508 0.00705 -0.0805 0.1279 0.7163
5.500 0.9750 0.01536 0.00732 -0.0802 0.1233 0.7182
5.750 0.9995 0.01569 0.00762 -0.0798 0.1188 0.7199
6.000 1.0243 0.01599 0.00791 -0.0794 0.1156 0.7216
6.250 1.0486 0.01627 0.00821 -0.0789 0.1128 0.7234
6.500 1.0721 0.01659 0.00854 -0.0783 0.1100 0.7253
6.750 1.0947 0.01695 0.00890 -0.0775 0.1075 0.7274
7.000 1.1168 0.01733 0.00929 -0.0767 0.1053 0.7297
7.250 1.1393 0.01765 0.00965 -0.0759 0.1038 0.7319
7.500 1.1609 0.01800 0.01004 -0.0750 0.1022 0.7341
7.750 1.1812 0.01839 0.01044 -0.0738 0.1004 0.7363
8.000 1.1981 0.01879 0.01086 -0.0721 0.0988 0.7386
8.250 1.2151 0.01927 0.01133 -0.0705 0.0972 0.7409
8.500 1.2325 0.01981 0.01191 -0.0690 0.0957 0.7432
8.750 1.2507 0.02034 0.01249 -0.0677 0.0946 0.7454
9.000 1.2697 0.02084 0.01305 -0.0666 0.0937 0.7476
9.250 1.2883 0.02139 0.01365 -0.0655 0.0928 0.7500
9.500 1.3066 0.02196 0.01427 -0.0644 0.0917 0.7524
9.750 1.3244 0.02258 0.01493 -0.0634 0.0905 0.7550
10.000 1.3418 0.02325 0.01563 -0.0623 0.0894 0.7576
10.250 1.3586 0.02397 0.01638 -0.0612 0.0884 0.7603
10.500 1.3744 0.02475 0.01721 -0.0600 0.0874 0.7630
10.750 1.3890 0.02563 0.01812 -0.0588 0.0862 0.7656
11.000 1.4034 0.02655 0.01909 -0.0576 0.0852 0.7684
11.250 1.4208 0.02728 0.01990 -0.0567 0.0843 0.7713
11.500 1.4375 0.02806 0.02075 -0.0558 0.0831 0.7743
11.750 1.4537 0.02889 0.02164 -0.0550 0.0819 0.7773
12.000 1.4690 0.02981 0.02260 -0.0541 0.0808 0.7801
12.250 1.4834 0.03078 0.02363 -0.0531 0.0798 0.7830
12.500 1.4967 0.03185 0.02475 -0.0522 0.0788 0.7862
12.750 1.5090 0.03301 0.02597 -0.0511 0.0779 0.7896
13.000 1.5197 0.03433 0.02733 -0.0501 0.0770 0.7934
13.250 1.5320 0.03554 0.02861 -0.0492 0.0763 0.7972
13.500 1.5455 0.03665 0.02982 -0.0484 0.0755 0.8008
13.750 1.5582 0.03782 0.03109 -0.0475 0.0746 0.8048
14.000 1.5702 0.03908 0.03243 -0.0467 0.0737 0.8089
14.250 1.5817 0.04039 0.03383 -0.0460 0.0728 0.8131
14.750 1.6019 0.04332 0.03690 -0.0445 0.0710 0.8211
15.000 1.6104 0.04496 0.03860 -0.0438 0.0702 0.8257
15.250 1.6174 0.04678 0.04048 -0.0431 0.0694 0.8305
15.750 1.6337 0.05030 0.04420 -0.0419 0.0677 0.8400
16.000 1.6428 0.05202 0.04603 -0.0415 0.0668 0.8454
16.250 1.6506 0.05391 0.04802 -0.0411 0.0657 0.8510
16.500 1.6575 0.05588 0.05008 -0.0408 0.0647 0.8567
16.750 1.6631 0.05805 0.05235 -0.0405 0.0638 0.8635
17.000 1.6676 0.06039 0.05477 -0.0403 0.0629 0.8703
17.250 1.6703 0.06295 0.05741 -0.0402 0.0621 0.8781
17.500 1.6724 0.06563 0.06019 -0.0401 0.0612 0.8864
17.750 1.6763 0.06807 0.06277 -0.0401 0.0604 0.8965
18.000 1.6788 0.07063 0.06546 -0.0400 0.0594 0.9088
18.500 1.6756 0.07630 0.07138 -0.0396 0.0575 1.0000
18.750 1.6748 0.07971 0.07486 -0.0403 0.0565 1.0000
19.000 1.6717 0.08348 0.07870 -0.0413 0.0556 1.0000
19.250 1.6677 0.08739 0.08271 -0.0423 0.0547 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)