NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Reynolds number: 200,000 Max Cl/Cd: 48.53 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ms317-il-200000.txt Download as CSV file: xf-ms317-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5797 0.08953 0.08539 -0.0633 1.0000 0.0516
-14.500 -0.5697 0.08797 0.08386 -0.0634 1.0000 0.0523
-14.250 -0.9042 0.05918 0.05355 -0.0733 1.0000 0.0459
-14.000 -0.9118 0.05595 0.05018 -0.0734 1.0000 0.0462
-13.750 -0.9170 0.05308 0.04717 -0.0731 1.0000 0.0465
-13.500 -0.9206 0.05054 0.04451 -0.0726 1.0000 0.0470
-13.250 -0.9253 0.04809 0.04191 -0.0717 1.0000 0.0475
-13.000 -0.9312 0.04573 0.03937 -0.0703 1.0000 0.0481
-12.750 -0.9387 0.04358 0.03702 -0.0681 1.0000 0.0487
-12.500 -0.9491 0.04179 0.03505 -0.0648 1.0000 0.0492
-12.250 -0.9589 0.04020 0.03326 -0.0611 1.0000 0.0497
-12.000 -0.9697 0.03894 0.03180 -0.0566 1.0000 0.0501
-11.750 -0.9827 0.03800 0.03066 -0.0515 1.0000 0.0505
-11.500 -0.9827 0.03670 0.02932 -0.0480 1.0000 0.0510
-11.250 -0.9789 0.03581 0.02845 -0.0449 1.0000 0.0517
-11.000 -0.9586 0.03468 0.02728 -0.0450 0.9981 0.0528
-10.750 -0.9262 0.03331 0.02580 -0.0472 0.9947 0.0544
-10.500 -0.8948 0.03189 0.02408 -0.0493 0.9909 0.0564
-10.250 -0.8621 0.03050 0.02273 -0.0511 0.9872 0.0583
-10.000 -0.8275 0.02946 0.02168 -0.0533 0.9836 0.0605
-9.750 -0.7916 0.02834 0.02039 -0.0556 0.9809 0.0630
-9.500 -0.7606 0.02722 0.01932 -0.0568 0.9766 0.0654
-9.250 -0.7272 0.02640 0.01849 -0.0587 0.9721 0.0686
-9.000 -0.6912 0.02537 0.01739 -0.0609 0.9692 0.0722
-8.750 -0.6536 0.02446 0.01657 -0.0635 0.9670 0.0763
-8.500 -0.6246 0.02364 0.01571 -0.0643 0.9613 0.0809
-8.250 -0.5909 0.02284 0.01498 -0.0663 0.9572 0.0867
-8.000 -0.5562 0.02190 0.01411 -0.0684 0.9540 0.0935
-7.750 -0.5205 0.02102 0.01326 -0.0707 0.9513 0.1024
-7.500 -0.4967 0.02055 0.01276 -0.0706 0.9437 0.1111
-7.250 -0.4667 0.01976 0.01208 -0.0719 0.9391 0.1223
-7.000 -0.4345 0.01901 0.01141 -0.0735 0.9356 0.1358
-6.750 -0.4105 0.01844 0.01093 -0.0736 0.9290 0.1502
-6.500 -0.3835 0.01780 0.01040 -0.0742 0.9231 0.1693
-6.250 -0.3539 0.01702 0.00980 -0.0755 0.9188 0.1976
-6.000 -0.3268 0.01624 0.00928 -0.0764 0.9137 0.2401
-5.750 -0.3017 0.01534 0.00877 -0.0773 0.9072 0.3100
-5.500 -0.2721 0.01412 0.00828 -0.0792 0.9027 0.4384
-5.250 -0.2427 0.01392 0.00856 -0.0792 0.8990 0.5428
-5.000 -0.2156 0.01424 0.00895 -0.0787 0.8932 0.5869
-4.750 -0.1878 0.01463 0.00934 -0.0782 0.8876 0.6123
-4.500 -0.1586 0.01500 0.00966 -0.0778 0.8832 0.6310
-4.250 -0.1285 0.01534 0.00991 -0.0776 0.8796 0.6464
-4.000 -0.1037 0.01590 0.01048 -0.0764 0.8737 0.6568
-3.750 -0.0768 0.01630 0.01084 -0.0757 0.8683 0.6669
-3.500 -0.0505 0.01676 0.01128 -0.0745 0.8641 0.6752
-3.250 -0.0214 0.01702 0.01147 -0.0742 0.8607 0.6848
-3.000 0.0012 0.01765 0.01213 -0.0722 0.8556 0.6910
-2.750 0.0288 0.01797 0.01240 -0.0721 0.8497 0.7026
-2.500 0.0506 0.01852 0.01298 -0.0694 0.8452 0.7074
-2.250 0.0763 0.01885 0.01328 -0.0680 0.8415 0.7138
-2.000 0.1056 0.01896 0.01334 -0.0685 0.8371 0.7229
-1.750 0.1254 0.01946 0.01389 -0.0660 0.8310 0.7271
-1.500 0.1493 0.01979 0.01422 -0.0643 0.8262 0.7339
-1.250 0.1786 0.01984 0.01422 -0.0644 0.8226 0.7432
-1.000 0.2002 0.02017 0.01456 -0.0620 0.8188 0.7474
-0.750 0.2232 0.02036 0.01478 -0.0610 0.8114 0.7529
-0.500 0.2601 0.02003 0.01436 -0.0638 0.8060 0.7603
-0.250 0.2866 0.01980 0.01410 -0.0627 0.8015 0.7628
0.000 0.3090 0.01970 0.01402 -0.0612 0.7913 0.7654
0.250 0.3380 0.01916 0.01339 -0.0601 0.7822 0.7686
0.500 0.3648 0.01886 0.01307 -0.0597 0.7699 0.7727
0.750 0.3998 0.01844 0.01254 -0.0612 0.7626 0.7775
1.000 0.4285 0.01823 0.01235 -0.0616 0.7531 0.7812
1.250 0.4550 0.01795 0.01204 -0.0607 0.7450 0.7833
1.500 0.4808 0.01779 0.01189 -0.0600 0.7358 0.7860
1.750 0.5091 0.01755 0.01162 -0.0598 0.7263 0.7894
2.000 0.5390 0.01733 0.01140 -0.0602 0.7161 0.7931
2.250 0.5729 0.01702 0.01103 -0.0616 0.7054 0.7966
2.500 0.6019 0.01681 0.01084 -0.0619 0.6928 0.7997
2.750 0.6273 0.01659 0.01061 -0.0610 0.6811 0.8021
3.000 0.6535 0.01639 0.01041 -0.0603 0.6670 0.8047
3.250 0.6806 0.01623 0.01025 -0.0601 0.6496 0.8074
3.500 0.7090 0.01607 0.01006 -0.0602 0.6288 0.8105
3.750 0.7379 0.01599 0.00993 -0.0606 0.6004 0.8142
4.000 0.7661 0.01598 0.00978 -0.0608 0.5600 0.8173
4.250 0.7847 0.01617 0.00968 -0.0589 0.4975 0.8195
4.500 0.7960 0.01689 0.00989 -0.0559 0.4117 0.8223
4.750 0.8066 0.01783 0.01039 -0.0533 0.3383 0.8255
5.000 0.8209 0.01872 0.01092 -0.0516 0.2852 0.8287
5.250 0.8393 0.01950 0.01146 -0.0508 0.2505 0.8317
5.500 0.8604 0.02026 0.01200 -0.0505 0.2271 0.8346
5.750 0.8761 0.02076 0.01243 -0.0486 0.2122 0.8370
6.000 0.8927 0.02131 0.01293 -0.0469 0.2009 0.8399
6.250 0.9097 0.02195 0.01346 -0.0455 0.1917 0.8429
6.500 0.9305 0.02246 0.01398 -0.0447 0.1840 0.8459
6.750 0.9509 0.02304 0.01450 -0.0441 0.1774 0.8489
7.000 0.9738 0.02376 0.01515 -0.0440 0.1716 0.8517
7.250 0.9917 0.02416 0.01560 -0.0426 0.1668 0.8542
7.500 1.0102 0.02469 0.01612 -0.0413 0.1627 0.8572
7.750 1.0340 0.02556 0.01685 -0.0411 0.1584 0.8605
8.000 1.0568 0.02606 0.01745 -0.0407 0.1556 0.8639
8.250 1.0820 0.02666 0.01810 -0.0408 0.1524 0.8670
8.500 1.1054 0.02725 0.01871 -0.0406 0.1493 0.8698
8.750 1.1270 0.02785 0.01929 -0.0399 0.1466 0.8729
9.000 1.1578 0.02881 0.02016 -0.0407 0.1435 0.8761
9.250 1.1795 0.02941 0.02089 -0.0402 0.1417 0.8801
9.500 1.2041 0.03013 0.02170 -0.0402 0.1396 0.8837
9.750 1.2257 0.03078 0.02243 -0.0396 0.1374 0.8869
10.000 1.2465 0.03143 0.02313 -0.0389 0.1352 0.8905
10.250 1.2705 0.03216 0.02386 -0.0388 0.1332 0.8944
10.500 1.3035 0.03324 0.02489 -0.0402 0.1310 0.8983
10.750 1.3291 0.03438 0.02613 -0.0404 0.1291 0.9024
11.000 1.3424 0.03509 0.02700 -0.0386 0.1277 0.9075
11.250 1.3599 0.03597 0.02803 -0.0376 0.1259 0.9126
11.500 1.3765 0.03685 0.02904 -0.0365 0.1241 0.9176
11.750 1.3918 0.03766 0.02994 -0.0352 0.1223 0.9234
12.000 1.4112 0.03853 0.03083 -0.0347 0.1204 0.9295
12.250 1.4341 0.03945 0.03172 -0.0345 0.1186 0.9359
12.500 1.4545 0.04105 0.03342 -0.0342 0.1167 0.9435
12.750 1.4558 0.04196 0.03456 -0.0311 0.1155 0.9557
13.000 1.4589 0.04301 0.03582 -0.0286 0.1141 0.9796
13.250 1.4705 0.04441 0.03739 -0.0280 0.1123 1.0000
13.500 1.4837 0.04586 0.03895 -0.0278 0.1106 1.0000
13.750 1.4981 0.04723 0.04040 -0.0276 0.1089 1.0000
14.000 1.5208 0.04844 0.04155 -0.0283 0.1072 1.0000
14.250 1.5417 0.05073 0.04389 -0.0289 0.1054 1.0000
14.500 1.5340 0.05302 0.04647 -0.0270 0.1044 1.0000
14.750 1.5262 0.05564 0.04936 -0.0255 0.1032 1.0000
15.000 1.5198 0.05838 0.05232 -0.0243 0.1018 1.0000
15.250 1.5169 0.06097 0.05508 -0.0236 0.1004 1.0000
15.500 1.5188 0.06321 0.05742 -0.0231 0.0990 1.0000
15.750 1.5223 0.06531 0.05958 -0.0228 0.0977 1.0000
16.000 1.5357 0.06678 0.06102 -0.0228 0.0964 1.0000
16.250 1.5442 0.06957 0.06383 -0.0227 0.0949 1.0000
16.500 1.5114 0.07475 0.06935 -0.0221 0.0943 1.0000
16.750 1.4734 0.08112 0.07605 -0.0226 0.0938 1.0000
17.000 1.4267 0.08938 0.08467 -0.0246 0.0933 1.0000
17.250 1.3572 0.10216 0.09787 -0.0299 0.0930 1.0000
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Polar data table (+)
Polar graphs
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