S6063 7.05% (s6063-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6063 7.05% (s6063-il) Reynolds number: 100,000 Max Cl/Cd: 45.33 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6063-il-100000-n5.txt Download as CSV file: xf-s6063-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6063 7.05%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5563 0.10709 0.10220 -0.0020 1.0000 0.0498
-9.000 -0.5565 0.10308 0.09824 -0.0054 1.0000 0.0500
-8.750 -0.5564 0.09888 0.09410 -0.0087 1.0000 0.0501
-8.500 -0.5401 0.09282 0.08797 -0.0045 1.0000 0.0322
-8.250 -0.5449 0.08598 0.08120 -0.0100 1.0000 0.0255
-8.000 -0.5441 0.08212 0.07738 -0.0117 1.0000 0.0247
-7.750 -0.5451 0.07768 0.07300 -0.0148 1.0000 0.0239
-7.500 -0.5426 0.07246 0.06779 -0.0196 1.0000 0.0231
-7.250 -0.5393 0.06634 0.06163 -0.0246 1.0000 0.0221
-6.750 -0.5268 0.05143 0.04615 -0.0333 1.0000 0.0191
-6.500 -0.5156 0.04711 0.04160 -0.0345 1.0000 0.0188
-6.250 -0.5023 0.04286 0.03705 -0.0352 1.0000 0.0185
-6.000 -0.4868 0.03876 0.03256 -0.0356 1.0000 0.0183
-5.750 -0.4693 0.03497 0.02833 -0.0355 1.0000 0.0180
-5.500 -0.4500 0.03160 0.02448 -0.0351 1.0000 0.0178
-5.250 -0.4289 0.02866 0.02094 -0.0344 1.0000 0.0184
-5.000 -0.4065 0.02635 0.01808 -0.0335 1.0000 0.0193
-4.750 -0.3851 0.02412 0.01560 -0.0328 1.0000 0.0204
-4.500 -0.3626 0.02231 0.01354 -0.0318 1.0000 0.0209
-4.250 -0.3401 0.02072 0.01175 -0.0307 1.0000 0.0214
-4.000 -0.3179 0.01937 0.01026 -0.0296 1.0000 0.0221
-3.750 -0.2960 0.01822 0.00900 -0.0284 1.0000 0.0229
-3.500 -0.2741 0.01722 0.00783 -0.0273 1.0000 0.0244
-3.250 -0.2522 0.01642 0.00687 -0.0262 1.0000 0.0262
-3.000 -0.2302 0.01563 0.00602 -0.0252 1.0000 0.0313
-2.750 -0.2080 0.01488 0.00528 -0.0242 1.0000 0.0455
-2.500 -0.1865 0.01373 0.00467 -0.0235 1.0000 0.1477
-2.250 -0.1662 0.01254 0.00442 -0.0229 1.0000 0.3566
-2.000 -0.1496 0.01146 0.00444 -0.0207 1.0000 0.6131
-1.750 -0.1268 0.01097 0.00450 -0.0185 0.9951 0.8027
-1.500 -0.0765 0.01079 0.00432 -0.0221 0.9920 0.9534
-1.250 -0.0271 0.01079 0.00404 -0.0268 0.9854 1.0000
-1.000 0.0129 0.01084 0.00390 -0.0296 0.9757 1.0000
-0.750 0.0537 0.01090 0.00378 -0.0325 0.9663 1.0000
-0.500 0.0949 0.01094 0.00368 -0.0354 0.9572 1.0000
-0.250 0.1319 0.01097 0.00361 -0.0373 0.9452 1.0000
0.000 0.1674 0.01100 0.00356 -0.0389 0.9323 1.0000
0.250 0.2014 0.01103 0.00353 -0.0400 0.9183 1.0000
0.500 0.2335 0.01106 0.00351 -0.0407 0.9035 1.0000
0.750 0.2637 0.01108 0.00350 -0.0409 0.8878 1.0000
1.000 0.2910 0.01113 0.00353 -0.0405 0.8696 1.0000
1.250 0.3181 0.01117 0.00355 -0.0400 0.8510 1.0000
1.500 0.3448 0.01121 0.00359 -0.0394 0.8322 1.0000
1.750 0.3701 0.01127 0.00365 -0.0385 0.8106 1.0000
2.000 0.3957 0.01133 0.00371 -0.0375 0.7888 1.0000
2.250 0.4207 0.01141 0.00379 -0.0366 0.7643 1.0000
2.500 0.4457 0.01151 0.00391 -0.0355 0.7377 1.0000
2.750 0.4706 0.01163 0.00402 -0.0345 0.7089 1.0000
3.000 0.4953 0.01178 0.00414 -0.0334 0.6775 1.0000
3.250 0.5200 0.01197 0.00431 -0.0324 0.6425 1.0000
3.500 0.5445 0.01220 0.00454 -0.0313 0.6041 1.0000
3.750 0.5680 0.01253 0.00473 -0.0301 0.5533 1.0000
4.000 0.5895 0.01306 0.00491 -0.0286 0.4697 1.0000
4.250 0.6116 0.01368 0.00522 -0.0275 0.3896 1.0000
4.500 0.6325 0.01458 0.00568 -0.0265 0.2878 1.0000
4.750 0.6526 0.01581 0.00627 -0.0258 0.1675 1.0000
5.000 0.6724 0.01738 0.00719 -0.0250 0.0607 1.0000
5.250 0.6942 0.01869 0.00834 -0.0242 0.0363 1.0000
5.500 0.7175 0.01963 0.00940 -0.0235 0.0290 1.0000
5.750 0.7397 0.02074 0.01064 -0.0226 0.0257 1.0000
6.000 0.7619 0.02185 0.01201 -0.0218 0.0243 1.0000
6.250 0.7834 0.02309 0.01343 -0.0208 0.0232 1.0000
6.500 0.8047 0.02450 0.01497 -0.0198 0.0224 1.0000
6.750 0.8262 0.02607 0.01669 -0.0189 0.0218 1.0000
7.000 0.8481 0.02785 0.01864 -0.0180 0.0213 1.0000
7.250 0.8700 0.02986 0.02085 -0.0171 0.0210 1.0000
7.500 0.8914 0.03216 0.02342 -0.0162 0.0207 1.0000
7.750 0.9112 0.03468 0.02626 -0.0153 0.0204 1.0000
8.000 0.9278 0.03763 0.02946 -0.0145 0.0196 1.0000
8.250 0.9419 0.04061 0.03301 -0.0133 0.0189 1.0000
8.500 0.9533 0.04383 0.03675 -0.0120 0.0185 1.0000
8.750 0.9605 0.04752 0.04090 -0.0108 0.0184 1.0000
9.000 0.9631 0.05146 0.04528 -0.0096 0.0184 1.0000
9.250 0.9612 0.05550 0.04969 -0.0085 0.0185 1.0000
9.500 0.9541 0.05959 0.05409 -0.0076 0.0185 1.0000
9.750 0.9411 0.06349 0.05822 -0.0067 0.0186 1.0000
10.000 0.9247 0.06760 0.06251 -0.0068 0.0187 1.0000
10.250 0.9077 0.07247 0.06753 -0.0090 0.0188 1.0000
10.500 0.8902 0.07854 0.07372 -0.0132 0.0189 1.0000
10.750 0.8737 0.08593 0.08120 -0.0191 0.0190 1.0000
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Polar data table (+)
Polar graphs
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