NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il) Reynolds number: 500,000 Max Cl/Cd: 63.05 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20714-il-500000.txt Download as CSV file: xf-sc20714-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0714 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
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9204 0.10182 0.09834 -0.0570 1.0000 0.0315
-18.000 -0.9840 0.08595 0.08213 -0.0669 1.0000 0.0313
-17.750 -1.0141 0.07728 0.07322 -0.0719 1.0000 0.0314
-17.500 -1.0351 0.07070 0.06644 -0.0754 1.0000 0.0315
-17.250 -1.0510 0.06534 0.06090 -0.0778 1.0000 0.0316
-17.000 -1.0635 0.06083 0.05622 -0.0795 1.0000 0.0318
-16.750 -1.0735 0.05697 0.05219 -0.0805 1.0000 0.0320
-16.500 -1.0816 0.05364 0.04870 -0.0810 1.0000 0.0322
-16.250 -1.0881 0.05076 0.04568 -0.0810 1.0000 0.0324
-16.000 -1.0937 0.04827 0.04304 -0.0805 1.0000 0.0325
-15.750 -1.0983 0.04572 0.04036 -0.0796 1.0000 0.0328
-15.500 -1.0971 0.04380 0.03840 -0.0784 1.0000 0.0332
-15.250 -1.0950 0.04225 0.03682 -0.0771 1.0000 0.0335
-15.000 -1.0931 0.04085 0.03538 -0.0756 1.0000 0.0338
-14.750 -1.0921 0.03952 0.03401 -0.0738 1.0000 0.0341
-14.500 -1.0915 0.03827 0.03272 -0.0718 1.0000 0.0344
-14.250 -1.0917 0.03708 0.03147 -0.0695 1.0000 0.0347
-14.000 -1.0923 0.03596 0.03029 -0.0670 1.0000 0.0351
-13.750 -1.0937 0.03488 0.02915 -0.0642 1.0000 0.0354
-13.500 -1.0957 0.03387 0.02808 -0.0612 1.0000 0.0358
-13.250 -1.0992 0.03295 0.02708 -0.0578 1.0000 0.0362
-13.000 -1.1054 0.03211 0.02618 -0.0539 1.0000 0.0365
-12.750 -1.1138 0.03134 0.02533 -0.0495 1.0000 0.0368
-12.500 -1.1102 0.03046 0.02436 -0.0472 1.0000 0.0372
-12.250 -1.1028 0.02936 0.02319 -0.0453 1.0000 0.0377
-12.000 -1.0797 0.02823 0.02208 -0.0461 0.9988 0.0386
-11.750 -1.0529 0.02734 0.02118 -0.0476 0.9972 0.0393
-11.500 -1.0246 0.02649 0.02030 -0.0494 0.9956 0.0402
-11.250 -0.9951 0.02568 0.01942 -0.0513 0.9942 0.0412
-11.000 -0.9648 0.02493 0.01860 -0.0532 0.9931 0.0422
-10.750 -0.9391 0.02411 0.01770 -0.0540 0.9914 0.0430
-10.500 -0.9143 0.02319 0.01682 -0.0548 0.9894 0.0443
-10.250 -0.8852 0.02257 0.01621 -0.0564 0.9876 0.0456
-10.000 -0.8548 0.02199 0.01559 -0.0581 0.9860 0.0470
-9.750 -0.8231 0.02146 0.01499 -0.0599 0.9847 0.0483
-9.500 -0.7922 0.02060 0.01416 -0.0617 0.9836 0.0500
-9.250 -0.7582 0.02005 0.01363 -0.0641 0.9826 0.0517
-9.000 -0.7232 0.01959 0.01315 -0.0664 0.9818 0.0536
-8.750 -0.6878 0.01919 0.01270 -0.0688 0.9811 0.0555
-8.500 -0.6622 0.01846 0.01202 -0.0695 0.9779 0.0577
-8.250 -0.6306 0.01803 0.01159 -0.0711 0.9758 0.0601
-8.000 -0.5977 0.01767 0.01120 -0.0729 0.9743 0.0623
-7.750 -0.5626 0.01701 0.01058 -0.0755 0.9732 0.0653
-7.500 -0.5272 0.01662 0.01020 -0.0778 0.9721 0.0686
-7.250 -0.4906 0.01622 0.00979 -0.0804 0.9711 0.0721
-7.000 -0.4526 0.01573 0.00936 -0.0833 0.9704 0.0768
-6.750 -0.4148 0.01537 0.00901 -0.0860 0.9697 0.0819
-6.500 -0.3769 0.01501 0.00870 -0.0888 0.9692 0.0890
-6.250 -0.3384 0.01461 0.00837 -0.0917 0.9687 0.0982
-6.000 -0.2992 0.01422 0.00806 -0.0948 0.9682 0.1109
-5.750 -0.2593 0.01384 0.00779 -0.0980 0.9678 0.1310
-5.500 -0.2312 0.01342 0.00754 -0.0989 0.9638 0.1594
-5.250 -0.1894 0.01283 0.00722 -0.1030 0.9632 0.2159
-5.000 -0.1205 0.01150 0.00658 -0.1139 0.9680 0.3698
-4.750 -0.0695 0.01065 0.00640 -0.1203 0.9685 0.5271
-4.500 -0.0322 0.01069 0.00655 -0.1223 0.9678 0.5708
-4.250 -0.0102 0.01083 0.00671 -0.1210 0.9625 0.5876
-4.000 0.0227 0.01091 0.00676 -0.1219 0.9602 0.6018
-3.750 0.0569 0.01101 0.00686 -0.1230 0.9583 0.6135
-3.500 0.0916 0.01110 0.00697 -0.1242 0.9568 0.6221
-3.250 0.1273 0.01120 0.00708 -0.1255 0.9556 0.6301
-3.000 0.1658 0.01120 0.00705 -0.1276 0.9547 0.6360
-2.750 0.2056 0.01116 0.00706 -0.1296 0.9538 0.6405
-2.500 0.2278 0.01127 0.00720 -0.1279 0.9464 0.6459
-2.250 0.2720 0.01105 0.00698 -0.1307 0.9437 0.6537
-2.000 0.3121 0.01079 0.00680 -0.1319 0.9402 0.6581
-1.750 0.3423 0.01073 0.00678 -0.1315 0.9343 0.6620
-1.500 0.3728 0.01061 0.00667 -0.1312 0.9267 0.6671
-1.250 0.4096 0.01031 0.00632 -0.1326 0.9195 0.6712
-1.000 0.4364 0.01017 0.00622 -0.1319 0.9111 0.6729
-0.750 0.4665 0.01001 0.00607 -0.1318 0.9026 0.6743
-0.500 0.4943 0.00991 0.00597 -0.1312 0.8899 0.6757
-0.250 0.5225 0.00983 0.00590 -0.1308 0.8757 0.6771
0.000 0.5513 0.00977 0.00583 -0.1306 0.8584 0.6787
0.250 0.5807 0.00975 0.00574 -0.1304 0.8362 0.6806
0.500 0.6088 0.00978 0.00567 -0.1301 0.7995 0.6826
0.750 0.6343 0.01006 0.00560 -0.1291 0.7227 0.6850
1.000 0.6514 0.01099 0.00578 -0.1268 0.5786 0.6874
1.250 0.6702 0.01199 0.00609 -0.1252 0.4407 0.6893
1.500 0.6914 0.01277 0.00635 -0.1242 0.3325 0.6908
2.000 0.7365 0.01405 0.00688 -0.1224 0.1819 0.6930
2.250 0.7611 0.01453 0.00715 -0.1218 0.1447 0.6940
2.500 0.7869 0.01489 0.00740 -0.1213 0.1224 0.6951
2.750 0.8129 0.01524 0.00766 -0.1209 0.1069 0.6963
3.000 0.8390 0.01557 0.00793 -0.1206 0.0965 0.6975
3.250 0.8649 0.01595 0.00824 -0.1201 0.0885 0.6988
3.500 0.8918 0.01620 0.00848 -0.1199 0.0831 0.7004
3.750 0.9175 0.01660 0.00884 -0.1194 0.0783 0.7021
4.000 0.9446 0.01685 0.00909 -0.1193 0.0749 0.7037
4.250 0.9710 0.01720 0.00939 -0.1190 0.0714 0.7052
4.500 0.9969 0.01761 0.00979 -0.1187 0.0685 0.7067
4.750 1.0238 0.01791 0.01010 -0.1185 0.0661 0.7081
5.000 1.0500 0.01827 0.01043 -0.1182 0.0637 0.7093
5.250 1.0728 0.01886 0.01099 -0.1173 0.0612 0.7106
5.500 1.0984 0.01908 0.01128 -0.1167 0.0594 0.7118
5.750 1.1231 0.01940 0.01162 -0.1160 0.0572 0.7129
6.000 1.1466 0.01981 0.01203 -0.1152 0.0553 0.7141
6.250 1.1680 0.02046 0.01269 -0.1139 0.0534 0.7155
6.500 1.1920 0.02082 0.01312 -0.1131 0.0518 0.7170
6.750 1.2154 0.02122 0.01354 -0.1122 0.0501 0.7185
7.000 1.2378 0.02173 0.01403 -0.1112 0.0485 0.7200
7.250 1.2584 0.02249 0.01481 -0.1099 0.0470 0.7215
7.500 1.2816 0.02291 0.01530 -0.1090 0.0456 0.7231
7.750 1.3040 0.02337 0.01578 -0.1081 0.0442 0.7248
8.000 1.3254 0.02390 0.01630 -0.1069 0.0430 0.7264
8.250 1.3437 0.02487 0.01725 -0.1054 0.0418 0.7278
8.500 1.3639 0.02553 0.01798 -0.1041 0.0410 0.7292
8.750 1.3832 0.02608 0.01863 -0.1025 0.0401 0.7306
9.000 1.4007 0.02670 0.01933 -0.1006 0.0392 0.7319
9.250 1.4152 0.02732 0.02002 -0.0982 0.0385 0.7334
9.500 1.4297 0.02799 0.02073 -0.0959 0.0378 0.7349
9.750 1.4451 0.02881 0.02157 -0.0939 0.0371 0.7366
10.000 1.4601 0.03021 0.02300 -0.0920 0.0363 0.7383
10.250 1.4756 0.03089 0.02380 -0.0900 0.0358 0.7401
10.500 1.4908 0.03170 0.02472 -0.0881 0.0352 0.7419
10.750 1.5052 0.03262 0.02574 -0.0861 0.0346 0.7438
11.000 1.5190 0.03359 0.02680 -0.0841 0.0340 0.7456
11.250 1.5321 0.03461 0.02788 -0.0821 0.0335 0.7472
11.500 1.5443 0.03561 0.02895 -0.0801 0.0331 0.7488
11.750 1.5552 0.03669 0.03010 -0.0779 0.0327 0.7502
12.000 1.5653 0.03791 0.03138 -0.0757 0.0323 0.7517
12.250 1.5737 0.03949 0.03302 -0.0735 0.0319 0.7532
12.500 1.5796 0.04149 0.03516 -0.0710 0.0315 0.7549
12.750 1.5850 0.04303 0.03686 -0.0686 0.0313 0.7569
13.000 1.5892 0.04475 0.03874 -0.0662 0.0310 0.7589
13.250 1.5921 0.04666 0.04082 -0.0640 0.0307 0.7610
13.500 1.5937 0.04877 0.04307 -0.0618 0.0304 0.7629
13.750 1.5940 0.05103 0.04549 -0.0599 0.0302 0.7646
14.000 1.5930 0.05346 0.04807 -0.0580 0.0299 0.7661
14.250 1.5903 0.05608 0.05085 -0.0564 0.0296 0.7676
14.500 1.5865 0.05888 0.05381 -0.0550 0.0294 0.7690
14.750 1.5820 0.06186 0.05694 -0.0539 0.0291 0.7705
15.000 1.5763 0.06516 0.06038 -0.0532 0.0289 0.7720
15.250 1.5697 0.06875 0.06411 -0.0530 0.0287 0.7736
15.500 1.5630 0.07256 0.06805 -0.0532 0.0285 0.7753
15.750 1.5530 0.07714 0.07277 -0.0540 0.0284 0.7770
16.000 1.5431 0.08195 0.07772 -0.0554 0.0282 0.7786
16.250 1.5292 0.08773 0.08365 -0.0575 0.0282 0.7801
16.500 1.5144 0.09396 0.09003 -0.0604 0.0280 0.7815
16.750 1.4935 0.10167 0.09793 -0.0646 0.0280 0.7825
17.000 1.4674 0.11092 0.10741 -0.0703 0.0279 0.7834
17.250 1.4167 0.12628 0.12313 -0.0812 0.0280 0.7833
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