NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il) Reynolds number: 100,000 Max Cl/Cd: 27.43 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20714-il-100000.txt Download as CSV file: xf-sc20714-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6453 0.09096 0.08500 -0.0551 1.0000 0.1158
-11.500 -0.7461 0.07622 0.07006 -0.0586 1.0000 0.1021
-11.250 -0.7616 0.07243 0.06627 -0.0568 1.0000 0.1010
-11.000 -0.7922 0.06908 0.06288 -0.0537 1.0000 0.1000
-10.750 -0.8216 0.06474 0.05843 -0.0523 1.0000 0.0987
-10.500 -0.8457 0.05988 0.05330 -0.0518 1.0000 0.0974
-10.250 -0.8564 0.05552 0.04862 -0.0514 1.0000 0.0971
-10.000 -0.8569 0.05164 0.04442 -0.0514 1.0000 0.0975
-9.750 -0.8503 0.04806 0.04047 -0.0516 1.0000 0.0984
-9.500 -0.8382 0.04467 0.03668 -0.0520 1.0000 0.0993
-9.250 -0.8215 0.04158 0.03316 -0.0526 1.0000 0.1004
-9.000 -0.8009 0.03902 0.03013 -0.0534 1.0000 0.1022
-8.750 -0.7798 0.03657 0.02746 -0.0537 1.0000 0.1047
-8.500 -0.7584 0.03509 0.02599 -0.0534 1.0000 0.1076
-8.250 -0.7353 0.03362 0.02438 -0.0533 1.0000 0.1106
-8.000 -0.7105 0.03218 0.02267 -0.0534 1.0000 0.1141
-7.750 -0.6861 0.03070 0.02104 -0.0535 1.0000 0.1180
-7.500 -0.6628 0.02965 0.02005 -0.0531 1.0000 0.1224
-7.250 -0.6379 0.02870 0.01899 -0.0529 1.0000 0.1274
-7.000 -0.6137 0.02764 0.01790 -0.0524 1.0000 0.1329
-6.750 -0.5901 0.02683 0.01719 -0.0519 1.0000 0.1392
-6.500 -0.5647 0.02608 0.01633 -0.0517 1.0000 0.1467
-6.250 -0.5418 0.02528 0.01576 -0.0509 1.0000 0.1554
-6.000 -0.5176 0.02456 0.01513 -0.0504 1.0000 0.1658
-5.750 -0.4924 0.02392 0.01462 -0.0502 1.0000 0.1805
-5.500 -0.4664 0.02321 0.01419 -0.0502 1.0000 0.2008
-5.250 -0.4364 0.02235 0.01374 -0.0513 1.0000 0.2410
-5.000 -0.4045 0.02114 0.01457 -0.0527 1.0000 0.4733
-4.750 -0.3999 0.02290 0.01658 -0.0455 1.0000 0.5681
-4.500 -0.3824 0.02432 0.01790 -0.0422 1.0000 0.6055
-4.250 -0.3713 0.02570 0.01924 -0.0372 1.0000 0.6245
-4.000 -0.3599 0.02693 0.02043 -0.0324 1.0000 0.6404
-3.750 -0.3462 0.02796 0.02139 -0.0285 1.0000 0.6557
-3.500 -0.3294 0.02882 0.02220 -0.0256 1.0000 0.6715
-3.250 -0.3266 0.02972 0.02312 -0.0186 1.0000 0.6788
-3.000 -0.3116 0.03038 0.02375 -0.0154 1.0000 0.6934
-2.750 -0.2929 0.03101 0.02432 -0.0134 1.0000 0.7097
-2.500 -0.2910 0.03143 0.02478 -0.0066 1.0000 0.7178
-2.250 -0.2751 0.03179 0.02511 -0.0040 1.0000 0.7324
-1.750 -0.2520 0.03241 0.02572 0.0034 1.0000 0.7625
-1.500 -0.2411 0.03272 0.02604 0.0073 1.0000 0.7820
-1.250 -0.2347 0.03272 0.02605 0.0122 1.0000 0.8004
-1.000 -0.2216 0.03269 0.02602 0.0149 1.0000 0.8161
-0.750 -0.2123 0.03218 0.02552 0.0184 1.0000 0.8251
-0.500 -0.1834 0.03233 0.02564 0.0163 1.0000 0.8326
-0.250 -0.1686 0.03197 0.02528 0.0181 1.0000 0.8386
0.000 -0.1280 0.03230 0.02559 0.0141 0.9946 0.8448
0.250 -0.0803 0.03256 0.02585 0.0092 0.9841 0.8499
0.500 -0.0384 0.03264 0.02594 0.0057 0.9729 0.8542
0.750 0.0065 0.03284 0.02615 0.0013 0.9615 0.8583
1.000 0.0574 0.03310 0.02643 -0.0042 0.9493 0.8616
1.250 0.1053 0.03291 0.02628 -0.0083 0.9351 0.8647
1.500 0.1547 0.03249 0.02591 -0.0123 0.9194 0.8677
1.750 0.2056 0.03179 0.02529 -0.0161 0.9008 0.8706
2.000 0.2602 0.03078 0.02435 -0.0201 0.8810 0.8732
2.250 0.3148 0.02965 0.02331 -0.0239 0.8629 0.8757
2.500 0.3650 0.02833 0.02210 -0.0266 0.8454 0.8781
2.750 0.4088 0.02666 0.02056 -0.0276 0.8264 0.8806
3.000 0.4535 0.02496 0.01898 -0.0286 0.8063 0.8823
3.250 0.4928 0.02341 0.01756 -0.0288 0.7772 0.8833
3.500 0.5320 0.02196 0.01615 -0.0287 0.7222 0.8845
3.750 0.5977 0.02179 0.01420 -0.0322 0.4061 0.8865
4.000 0.6065 0.02351 0.01484 -0.0296 0.2659 0.8878
4.250 0.6280 0.02467 0.01554 -0.0292 0.2160 0.8887
4.500 0.6544 0.02571 0.01627 -0.0297 0.1908 0.8894
4.750 0.6852 0.02671 0.01711 -0.0308 0.1734 0.8902
5.000 0.7188 0.02781 0.01800 -0.0325 0.1598 0.8911
5.250 0.7499 0.02855 0.01881 -0.0334 0.1501 0.8926
5.500 0.7823 0.02966 0.01978 -0.0346 0.1420 0.8944
5.750 0.8126 0.03048 0.02072 -0.0353 0.1346 0.8958
6.000 0.8485 0.03202 0.02207 -0.0374 0.1280 0.8969
6.250 0.8777 0.03296 0.02329 -0.0379 0.1225 0.8980
6.500 0.9084 0.03412 0.02448 -0.0389 0.1173 0.8991
6.750 0.9398 0.03594 0.02635 -0.0402 0.1128 0.9003
7.000 0.9666 0.03746 0.02824 -0.0404 0.1091 0.9017
7.250 0.9946 0.03899 0.02990 -0.0409 0.1053 0.9035
7.500 1.0249 0.04110 0.03195 -0.0424 0.1017 0.9053
7.750 1.0429 0.04326 0.03457 -0.0412 0.0996 0.9068
8.000 1.0593 0.04571 0.03750 -0.0398 0.0981 0.9081
8.250 1.0731 0.04844 0.04068 -0.0383 0.0966 0.9093
8.500 1.0846 0.05122 0.04385 -0.0367 0.0951 0.9105
8.750 1.0956 0.05395 0.04689 -0.0353 0.0934 0.9119
9.000 1.1037 0.05709 0.05034 -0.0338 0.0925 0.9132
9.250 1.0918 0.06210 0.05593 -0.0303 0.0938 0.9143
9.500 1.0713 0.06752 0.06186 -0.0267 0.0958 0.9154
9.750 1.0502 0.07233 0.06700 -0.0235 0.0976 0.9167
10.000 1.0366 0.07724 0.07211 -0.0219 0.0992 0.9182
10.250 1.0451 0.08231 0.07723 -0.0222 0.1005 0.9198
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Polar data table (+)
Polar graphs
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