NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 100,000 Max Cl/Cd: 16.29 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20402-il-100000.txt Download as CSV file: xf-sc20402-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0402 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6827 0.10404 0.09939 0.0275 1.0000 0.0469
-8.000 -0.6789 0.10035 0.09574 0.0252 1.0000 0.0487
-7.750 -0.6738 0.09656 0.09199 0.0215 1.0000 0.0505
-7.500 -0.6629 0.09236 0.08780 0.0137 1.0000 0.0524
-7.250 -0.6438 0.08806 0.08342 0.0012 1.0000 0.0534
-7.000 -0.6241 0.08447 0.07957 -0.0079 1.0000 0.0539
-6.750 -0.6285 0.07765 0.07306 0.0017 1.0000 0.0577
-6.500 -0.6130 0.07316 0.06851 -0.0020 1.0000 0.0619
-6.250 -0.5762 0.07004 0.06479 -0.0157 1.0000 0.0669
-6.000 -0.5733 0.06311 0.05818 -0.0120 1.0000 0.0705
-5.750 -0.5410 0.05898 0.05308 -0.0199 1.0000 0.0805
-5.500 -0.5299 0.05401 0.04834 -0.0184 1.0000 0.0869
-5.250 -0.5058 0.04971 0.04384 -0.0214 1.0000 0.0985
-5.000 -0.4562 0.03093 0.02532 -0.0231 1.0000 0.1222
-4.750 -0.4578 0.04215 0.03593 -0.0256 1.0000 0.1387
-4.500 -0.4350 0.03878 0.03244 -0.0270 1.0000 0.1753
-3.500 -0.2873 0.02535 0.01663 -0.0321 1.0000 0.0907
-3.250 -0.2515 0.02322 0.01374 -0.0306 1.0000 0.0530
-3.000 -0.2205 0.02132 0.01140 -0.0298 1.0000 0.0412
-2.750 -0.1923 0.01856 0.00856 -0.0295 1.0000 0.0363
-2.500 -0.1640 0.01686 0.00668 -0.0288 1.0000 0.0326
-2.250 -0.1364 0.01546 0.00524 -0.0282 1.0000 0.0310
-1.750 -0.0793 0.01297 0.00260 -0.0278 1.0000 0.0514
-1.500 -0.0731 0.00935 0.00210 -0.0223 1.0000 0.8796
-1.250 -0.0457 0.00906 0.00135 -0.0211 1.0000 1.0000
-1.000 -0.0179 0.00905 0.00111 -0.0212 1.0000 1.0000
-0.750 0.0096 0.00905 0.00097 -0.0212 1.0000 1.0000
-0.500 0.0370 0.00906 0.00091 -0.0212 1.0000 1.0000
-0.250 0.0643 0.00907 0.00093 -0.0212 1.0000 1.0000
0.000 0.0915 0.00909 0.00102 -0.0211 1.0000 1.0000
0.250 0.1187 0.00913 0.00119 -0.0210 1.0000 1.0000
0.500 0.1459 0.00916 0.00149 -0.0209 1.0000 1.0000
0.750 0.1945 0.01302 0.00268 -0.0241 0.0498 1.0000
1.250 0.2485 0.01553 0.00534 -0.0228 0.0308 1.0000
1.500 0.2760 0.01696 0.00681 -0.0221 0.0324 1.0000
1.750 0.3047 0.01870 0.00871 -0.0214 0.0361 1.0000
2.000 0.3330 0.02161 0.01169 -0.0210 0.0409 1.0000
2.250 0.3641 0.02327 0.01379 -0.0199 0.0526 1.0000
2.500 0.3997 0.02523 0.01652 -0.0180 0.0892 1.0000
3.750 0.5579 0.04085 0.03461 -0.0179 0.1496 1.0000
4.000 0.5787 0.04426 0.03813 -0.0182 0.1228 1.0000
4.250 0.5975 0.04851 0.04237 -0.0184 0.1071 1.0000
4.500 0.6171 0.05283 0.04680 -0.0191 0.0936 1.0000
4.750 0.6405 0.05611 0.05046 -0.0208 0.0815 1.0000
5.000 0.6656 0.06061 0.05579 -0.0242 0.0721 1.0000
5.250 0.6743 0.06656 0.06157 -0.0227 0.0673 1.0000
5.500 0.7037 0.07014 0.06568 -0.0296 0.0623 1.0000
5.750 0.7202 0.07460 0.07026 -0.0322 0.0575 1.0000
6.000 0.7218 0.08122 0.07664 -0.0279 0.0540 1.0000
6.250 0.7381 0.08580 0.08143 -0.0329 0.0532 1.0000
6.500 0.7594 0.08964 0.08549 -0.0429 0.0514 1.0000
6.750 0.7715 0.09429 0.09019 -0.0489 0.0491 1.0000
7.000 0.7798 0.09888 0.09478 -0.0534 0.0472 1.0000
7.250 0.7856 0.10328 0.09918 -0.0568 0.0454 1.0000
7.500 0.7893 0.10749 0.10337 -0.0588 0.0438 1.0000
7.750 0.7929 0.11610 0.11194 -0.0472 0.0407 1.0000
8.000 0.7991 0.12016 0.11601 -0.0531 0.0406 1.0000
8.250 0.8011 0.12380 0.11961 -0.0581 0.0404 1.0000
8.500 0.8025 0.12717 0.12293 -0.0624 0.0403 1.0000
8.750 0.8038 0.13035 0.12607 -0.0663 0.0400 1.0000
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Polar data table (+)
Polar graphs
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