NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 500,000 Max Cl/Cd: 70.63 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20712-il-500000.txt Download as CSV file: xf-sc20712-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0712 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9764 0.06839 0.06466 -0.0657 1.0000 0.0254
-16.000 -0.9974 0.06189 0.05798 -0.0694 1.0000 0.0254
-15.750 -1.0122 0.05694 0.05286 -0.0717 1.0000 0.0255
-15.500 -1.0225 0.05294 0.04872 -0.0732 1.0000 0.0256
-15.250 -1.0299 0.04956 0.04521 -0.0740 1.0000 0.0258
-15.000 -1.0355 0.04659 0.04212 -0.0744 1.0000 0.0260
-14.750 -1.0402 0.04396 0.03937 -0.0742 1.0000 0.0262
-14.500 -1.0441 0.04163 0.03692 -0.0736 1.0000 0.0264
-14.250 -1.0477 0.03952 0.03470 -0.0724 1.0000 0.0266
-14.000 -1.0506 0.03772 0.03280 -0.0708 1.0000 0.0269
-13.750 -1.0551 0.03610 0.03108 -0.0685 1.0000 0.0271
-13.500 -1.0627 0.03472 0.02960 -0.0652 1.0000 0.0273
-13.250 -1.0724 0.03350 0.02829 -0.0612 1.0000 0.0276
-13.000 -1.0718 0.03209 0.02676 -0.0591 1.0000 0.0279
-12.750 -1.0668 0.03075 0.02529 -0.0576 1.0000 0.0282
-12.500 -1.0576 0.02952 0.02392 -0.0566 1.0000 0.0286
-12.250 -1.0447 0.02845 0.02270 -0.0560 1.0000 0.0289
-12.000 -1.0338 0.02661 0.02080 -0.0547 1.0000 0.0296
-11.750 -1.0171 0.02570 0.01987 -0.0543 1.0000 0.0303
-11.500 -0.9986 0.02494 0.01909 -0.0540 1.0000 0.0309
-11.250 -0.9793 0.02418 0.01827 -0.0537 1.0000 0.0317
-11.000 -0.9592 0.02341 0.01741 -0.0534 1.0000 0.0325
-10.750 -0.9380 0.02267 0.01657 -0.0532 1.0000 0.0332
-10.500 -0.9150 0.02207 0.01586 -0.0533 0.9999 0.0338
-10.250 -0.8859 0.02073 0.01453 -0.0548 0.9989 0.0352
-10.000 -0.8533 0.02013 0.01392 -0.0567 0.9977 0.0363
-9.750 -0.8206 0.01957 0.01332 -0.0586 0.9965 0.0376
-9.500 -0.7871 0.01908 0.01275 -0.0604 0.9954 0.0390
-9.250 -0.7542 0.01824 0.01190 -0.0624 0.9944 0.0406
-9.000 -0.7195 0.01780 0.01147 -0.0646 0.9936 0.0423
-8.750 -0.6871 0.01737 0.01102 -0.0662 0.9921 0.0441
-8.500 -0.6548 0.01701 0.01059 -0.0676 0.9904 0.0456
-8.250 -0.6213 0.01621 0.00983 -0.0697 0.9891 0.0479
-8.000 -0.5871 0.01585 0.00948 -0.0716 0.9877 0.0503
-7.750 -0.5524 0.01555 0.00913 -0.0735 0.9864 0.0527
-7.500 -0.5164 0.01489 0.00850 -0.0760 0.9855 0.0559
-7.250 -0.4809 0.01457 0.00820 -0.0781 0.9845 0.0593
-7.000 -0.4444 0.01414 0.00776 -0.0805 0.9838 0.0633
-6.750 -0.4076 0.01377 0.00743 -0.0829 0.9831 0.0682
-6.500 -0.3703 0.01343 0.00709 -0.0854 0.9825 0.0740
-6.250 -0.3363 0.01312 0.00682 -0.0871 0.9808 0.0804
-6.000 -0.3030 0.01277 0.00651 -0.0888 0.9785 0.0881
-5.750 -0.2682 0.01249 0.00627 -0.0906 0.9768 0.0980
-5.500 -0.2314 0.01211 0.00600 -0.0930 0.9756 0.1151
-5.250 -0.1931 0.01166 0.00575 -0.0959 0.9748 0.1524
-5.000 -0.1517 0.01100 0.00546 -0.0998 0.9745 0.2335
-4.750 -0.1062 0.01015 0.00514 -0.1049 0.9750 0.3597
-4.500 -0.0594 0.00938 0.00502 -0.1101 0.9759 0.5239
-4.250 -0.0237 0.00933 0.00512 -0.1117 0.9743 0.5761
-4.000 0.0115 0.00936 0.00514 -0.1133 0.9728 0.5982
-3.750 0.0467 0.00939 0.00519 -0.1147 0.9715 0.6112
-3.500 0.0828 0.00941 0.00522 -0.1164 0.9704 0.6216
-3.250 0.1201 0.00944 0.00523 -0.1183 0.9696 0.6322
-3.000 0.1457 0.00953 0.00535 -0.1176 0.9645 0.6393
-2.750 0.1792 0.00957 0.00540 -0.1186 0.9617 0.6475
-2.500 0.2156 0.00958 0.00546 -0.1200 0.9596 0.6570
-2.250 0.2599 0.00938 0.00528 -0.1230 0.9577 0.6653
-2.000 0.3043 0.00906 0.00499 -0.1258 0.9551 0.6724
-1.750 0.3313 0.00896 0.00494 -0.1249 0.9459 0.6766
-1.500 0.3683 0.00870 0.00468 -0.1261 0.9404 0.6808
-1.250 0.3973 0.00856 0.00451 -0.1258 0.9284 0.6856
-1.000 0.4251 0.00846 0.00443 -0.1252 0.9173 0.6889
-0.750 0.4531 0.00842 0.00442 -0.1246 0.9064 0.6919
-0.500 0.4813 0.00840 0.00441 -0.1242 0.8945 0.6946
-0.250 0.5101 0.00836 0.00436 -0.1241 0.8802 0.6970
0.000 0.5394 0.00833 0.00428 -0.1240 0.8619 0.6996
0.250 0.5681 0.00835 0.00421 -0.1238 0.8325 0.7024
0.500 0.5954 0.00843 0.00414 -0.1232 0.7871 0.7047
0.750 0.6174 0.00887 0.00414 -0.1214 0.6844 0.7064
1.000 0.6318 0.01014 0.00450 -0.1186 0.4926 0.7079
1.250 0.6508 0.01123 0.00490 -0.1171 0.3427 0.7096
1.500 0.6734 0.01204 0.00521 -0.1163 0.2396 0.7115
1.750 0.6980 0.01264 0.00549 -0.1158 0.1718 0.7136
2.000 0.7241 0.01311 0.00575 -0.1155 0.1340 0.7160
2.250 0.7511 0.01349 0.00600 -0.1154 0.1120 0.7185
2.500 0.7786 0.01385 0.00625 -0.1153 0.0968 0.7208
2.750 0.8054 0.01414 0.00650 -0.1151 0.0864 0.7228
3.000 0.8314 0.01446 0.00681 -0.1146 0.0781 0.7245
3.250 0.8567 0.01490 0.00719 -0.1140 0.0708 0.7262
3.500 0.8834 0.01516 0.00748 -0.1136 0.0662 0.7280
3.750 0.9083 0.01569 0.00796 -0.1130 0.0612 0.7299
4.000 0.9353 0.01594 0.00825 -0.1128 0.0583 0.7321
4.250 0.9618 0.01629 0.00857 -0.1125 0.0552 0.7344
4.500 0.9866 0.01688 0.00915 -0.1119 0.0523 0.7368
4.750 1.0137 0.01720 0.00948 -0.1117 0.0501 0.7389
5.000 1.0391 0.01752 0.00982 -0.1111 0.0479 0.7407
5.250 1.0618 0.01820 0.01050 -0.1101 0.0457 0.7424
5.500 1.0864 0.01865 0.01101 -0.1094 0.0443 0.7443
5.750 1.1112 0.01906 0.01147 -0.1087 0.0427 0.7463
6.000 1.1359 0.01948 0.01190 -0.1081 0.0411 0.7487
6.250 1.1587 0.02021 0.01261 -0.1072 0.0395 0.7513
6.500 1.1826 0.02086 0.01331 -0.1064 0.0383 0.7540
6.750 1.2073 0.02137 0.01388 -0.1058 0.0371 0.7563
7.000 1.2304 0.02189 0.01446 -0.1049 0.0360 0.7582
7.250 1.2528 0.02246 0.01506 -0.1038 0.0350 0.7603
7.500 1.2735 0.02340 0.01601 -0.1026 0.0339 0.7627
7.750 1.2948 0.02439 0.01710 -0.1014 0.0331 0.7652
8.000 1.3174 0.02504 0.01785 -0.1004 0.0323 0.7680
8.250 1.3397 0.02574 0.01863 -0.0994 0.0314 0.7706
8.500 1.3614 0.02639 0.01933 -0.0984 0.0305 0.7730
8.750 1.3815 0.02703 0.02002 -0.0971 0.0298 0.7749
9.000 1.4005 0.02798 0.02101 -0.0957 0.0292 0.7769
9.250 1.4178 0.02972 0.02285 -0.0941 0.0285 0.7790
9.500 1.4360 0.03057 0.02387 -0.0925 0.0281 0.7815
9.750 1.4532 0.03159 0.02504 -0.0908 0.0275 0.7842
10.000 1.4695 0.03271 0.02630 -0.0890 0.0270 0.7869
10.250 1.4843 0.03386 0.02757 -0.0871 0.0266 0.7893
10.500 1.4965 0.03501 0.02887 -0.0847 0.0262 0.7913
10.750 1.5068 0.03615 0.03014 -0.0820 0.0258 0.7936
11.000 1.5132 0.03725 0.03135 -0.0787 0.0255 0.7961
11.250 1.5194 0.03849 0.03269 -0.0756 0.0252 0.7990
11.500 1.5259 0.03991 0.03419 -0.0728 0.0249 0.8021
11.750 1.5305 0.04171 0.03609 -0.0700 0.0247 0.8047
12.000 1.5288 0.04434 0.03890 -0.0667 0.0244 0.8067
12.250 1.5200 0.04749 0.04231 -0.0629 0.0242 0.8087
12.500 1.5136 0.04982 0.04487 -0.0596 0.0241 0.8111
12.750 1.5053 0.05245 0.04774 -0.0567 0.0240 0.8135
13.000 1.4941 0.05563 0.05115 -0.0542 0.0238 0.8159
13.250 1.4801 0.05935 0.05510 -0.0523 0.0237 0.8183
13.500 1.4627 0.06374 0.05974 -0.0512 0.0236 0.8202
13.750 1.4414 0.06897 0.06523 -0.0510 0.0234 0.8219
14.000 1.4150 0.07556 0.07208 -0.0523 0.0234 0.8235
14.250 1.3850 0.08360 0.08038 -0.0556 0.0234 0.8250
14.500 1.3474 0.09456 0.09161 -0.0623 0.0235 0.8261
14.750 1.2940 0.11127 0.10863 -0.0744 0.0237 0.8262
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