NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il) Reynolds number: 200,000 Max Cl/Cd: 44.55 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20612-il-200000-n5.txt Download as CSV file: xf-sc20612-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0612 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8834 0.08485 0.07994 -0.0481 1.0000 0.0274
-15.250 -0.9214 0.07366 0.06847 -0.0557 1.0000 0.0273
-15.000 -0.9482 0.06594 0.06049 -0.0604 1.0000 0.0274
-14.750 -0.9687 0.05996 0.05426 -0.0634 1.0000 0.0275
-14.500 -0.9844 0.05509 0.04913 -0.0652 1.0000 0.0276
-14.250 -0.9926 0.05143 0.04529 -0.0661 1.0000 0.0278
-14.000 -0.9942 0.04874 0.04251 -0.0664 1.0000 0.0280
-13.750 -0.9940 0.04638 0.04006 -0.0664 1.0000 0.0283
-13.500 -0.9929 0.04424 0.03784 -0.0661 1.0000 0.0286
-13.250 -0.9914 0.04227 0.03577 -0.0655 1.0000 0.0289
-13.000 -0.9900 0.04044 0.03384 -0.0645 1.0000 0.0292
-12.750 -0.9891 0.03879 0.03209 -0.0631 1.0000 0.0296
-12.500 -0.9897 0.03730 0.03049 -0.0610 1.0000 0.0300
-12.250 -0.9913 0.03593 0.02901 -0.0585 1.0000 0.0305
-12.000 -0.9875 0.03448 0.02741 -0.0568 1.0000 0.0312
-11.750 -0.9808 0.03303 0.02578 -0.0553 1.0000 0.0319
-11.500 -0.9714 0.03169 0.02428 -0.0541 1.0000 0.0326
-11.250 -0.9594 0.03064 0.02322 -0.0531 1.0000 0.0331
-11.000 -0.9456 0.02968 0.02222 -0.0522 1.0000 0.0338
-10.750 -0.9305 0.02873 0.02120 -0.0514 1.0000 0.0346
-10.500 -0.9146 0.02777 0.02016 -0.0505 1.0000 0.0355
-10.250 -0.8976 0.02682 0.01909 -0.0496 1.0000 0.0365
-10.000 -0.8797 0.02590 0.01801 -0.0488 1.0000 0.0377
-9.750 -0.8610 0.02511 0.01724 -0.0482 1.0000 0.0387
-9.500 -0.8410 0.02445 0.01656 -0.0478 1.0000 0.0401
-9.250 -0.8203 0.02378 0.01582 -0.0474 1.0000 0.0417
-9.000 -0.7991 0.02309 0.01501 -0.0469 1.0000 0.0435
-8.750 -0.7775 0.02235 0.01428 -0.0467 1.0000 0.0450
-8.500 -0.7548 0.02176 0.01368 -0.0466 1.0000 0.0468
-8.250 -0.7267 0.02118 0.01303 -0.0474 0.9991 0.0495
-8.000 -0.6948 0.02050 0.01233 -0.0491 0.9974 0.0523
-7.750 -0.6622 0.01995 0.01177 -0.0508 0.9956 0.0553
-7.250 -0.5969 0.01885 0.01063 -0.0543 0.9926 0.0620
-7.000 -0.5650 0.01841 0.01016 -0.0558 0.9906 0.0660
-6.750 -0.5320 0.01790 0.00964 -0.0575 0.9885 0.0699
-6.500 -0.4982 0.01745 0.00922 -0.0594 0.9866 0.0746
-6.250 -0.4639 0.01706 0.00881 -0.0613 0.9849 0.0797
-6.000 -0.4286 0.01662 0.00840 -0.0635 0.9834 0.0862
-5.750 -0.3927 0.01622 0.00802 -0.0657 0.9820 0.0936
-5.500 -0.3603 0.01582 0.00766 -0.0672 0.9789 0.1023
-5.250 -0.3259 0.01540 0.00730 -0.0692 0.9765 0.1146
-5.000 -0.2907 0.01499 0.00699 -0.0713 0.9746 0.1321
-4.750 -0.2542 0.01452 0.00668 -0.0738 0.9731 0.1644
-4.500 -0.2157 0.01389 0.00636 -0.0771 0.9721 0.2246
-4.250 -0.1748 0.01310 0.00602 -0.0811 0.9715 0.3235
-4.000 -0.1330 0.01230 0.00590 -0.0851 0.9712 0.4616
-3.750 -0.0984 0.01227 0.00625 -0.0864 0.9698 0.5509
-3.500 -0.0696 0.01238 0.00641 -0.0864 0.9654 0.5829
-3.250 -0.0370 0.01246 0.00648 -0.0874 0.9623 0.6047
-3.000 -0.0037 0.01260 0.00662 -0.0883 0.9597 0.6234
-2.750 0.0300 0.01280 0.00685 -0.0892 0.9575 0.6404
-2.500 0.0653 0.01300 0.00705 -0.0904 0.9558 0.6553
-2.250 0.0881 0.01332 0.00743 -0.0888 0.9494 0.6649
-2.000 0.1199 0.01351 0.00764 -0.0893 0.9461 0.6747
-1.750 0.1521 0.01366 0.00783 -0.0898 0.9437 0.6805
-1.500 0.1889 0.01364 0.00780 -0.0917 0.9422 0.6856
-1.250 0.2218 0.01356 0.00771 -0.0928 0.9367 0.6899
-1.000 0.2551 0.01346 0.00766 -0.0933 0.9303 0.6925
-0.750 0.2906 0.01328 0.00752 -0.0943 0.9230 0.6955
-0.500 0.3285 0.01290 0.00715 -0.0955 0.9105 0.6983
-0.250 0.3600 0.01260 0.00684 -0.0956 0.8908 0.7009
0.000 0.3940 0.01231 0.00653 -0.0963 0.8688 0.7036
0.250 0.4289 0.01204 0.00617 -0.0972 0.8375 0.7066
0.500 0.4603 0.01193 0.00597 -0.0974 0.8016 0.7085
0.750 0.4887 0.01196 0.00589 -0.0968 0.7555 0.7102
1.000 0.5144 0.01220 0.00582 -0.0957 0.6752 0.7121
1.250 0.5330 0.01303 0.00592 -0.0934 0.5288 0.7142
1.500 0.5518 0.01400 0.00625 -0.0917 0.3981 0.7165
1.750 0.5742 0.01480 0.00657 -0.0909 0.2961 0.7187
2.000 0.5986 0.01548 0.00685 -0.0906 0.2198 0.7211
2.250 0.6252 0.01599 0.00711 -0.0907 0.1707 0.7237
2.500 0.6531 0.01644 0.00736 -0.0910 0.1389 0.7263
2.750 0.6785 0.01684 0.00768 -0.0905 0.1203 0.7277
3.000 0.7038 0.01723 0.00803 -0.0900 0.1076 0.7293
3.250 0.7292 0.01763 0.00840 -0.0895 0.0977 0.7312
3.500 0.7552 0.01799 0.00877 -0.0891 0.0901 0.7333
3.750 0.7806 0.01845 0.00916 -0.0887 0.0836 0.7357
4.000 0.8073 0.01879 0.00955 -0.0885 0.0784 0.7382
4.250 0.8336 0.01924 0.00996 -0.0883 0.0736 0.7409
4.500 0.8607 0.01967 0.01040 -0.0883 0.0696 0.7435
4.750 0.8872 0.02008 0.01083 -0.0881 0.0656 0.7456
5.000 0.9108 0.02063 0.01136 -0.0874 0.0623 0.7471
5.250 0.9357 0.02107 0.01189 -0.0867 0.0592 0.7489
5.500 0.9601 0.02155 0.01240 -0.0861 0.0561 0.7510
5.750 0.9838 0.02217 0.01302 -0.0854 0.0534 0.7533
6.000 1.0087 0.02270 0.01364 -0.0849 0.0506 0.7558
6.250 1.0334 0.02328 0.01425 -0.0844 0.0483 0.7583
6.500 1.0574 0.02400 0.01494 -0.0840 0.0463 0.7609
6.750 1.0826 0.02462 0.01568 -0.0836 0.0440 0.7633
7.000 1.1055 0.02522 0.01635 -0.0827 0.0420 0.7650
7.250 1.1278 0.02584 0.01701 -0.0818 0.0405 0.7668
7.500 1.1496 0.02667 0.01792 -0.0808 0.0392 0.7690
7.750 1.1720 0.02751 0.01890 -0.0799 0.0378 0.7716
8.000 1.1942 0.02831 0.01980 -0.0791 0.0365 0.7744
8.250 1.2162 0.02905 0.02058 -0.0783 0.0353 0.7773
8.500 1.2377 0.02987 0.02141 -0.0776 0.0344 0.7801
8.750 1.2575 0.03089 0.02262 -0.0763 0.0333 0.7819
9.000 1.2765 0.03195 0.02386 -0.0749 0.0323 0.7840
9.250 1.2947 0.03302 0.02509 -0.0735 0.0315 0.7864
9.500 1.3122 0.03407 0.02626 -0.0721 0.0308 0.7891
9.750 1.3291 0.03512 0.02740 -0.0706 0.0302 0.7920
10.000 1.3451 0.03624 0.02859 -0.0692 0.0297 0.7949
10.250 1.3594 0.03758 0.03001 -0.0675 0.0293 0.7975
10.500 1.3700 0.03928 0.03200 -0.0652 0.0288 0.7995
10.750 1.3775 0.04104 0.03405 -0.0626 0.0282 0.8018
11.000 1.3802 0.04273 0.03599 -0.0593 0.0277 0.8044
11.250 1.3831 0.04455 0.03804 -0.0563 0.0272 0.8073
11.500 1.3855 0.04642 0.04010 -0.0537 0.0268 0.8102
11.750 1.3871 0.04838 0.04226 -0.0513 0.0264 0.8132
12.000 1.3866 0.05044 0.04449 -0.0489 0.0261 0.8154
12.250 1.3851 0.05260 0.04682 -0.0467 0.0258 0.8179
12.500 1.3819 0.05508 0.04945 -0.0448 0.0256 0.8207
12.750 1.3766 0.05794 0.05248 -0.0433 0.0254 0.8237
13.000 1.3691 0.06125 0.05596 -0.0423 0.0253 0.8267
13.250 1.3588 0.06514 0.06002 -0.0419 0.0251 0.8295
13.500 1.3451 0.06966 0.06475 -0.0421 0.0250 0.8317
13.750 1.3250 0.07551 0.07084 -0.0436 0.0249 0.8337
14.000 1.2968 0.08350 0.07914 -0.0473 0.0249 0.8355
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