SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 200,000 Max Cl/Cd: 57.96 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7003-il-200000-n5.txt Download as CSV file: xf-sd7003-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7003-085-88
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6251 0.08127 0.07770 -0.0114 1.0000 0.0130
-9.750 -0.6499 0.07141 0.06791 -0.0174 1.0000 0.0128
-9.250 -0.7112 0.04793 0.04418 -0.0370 1.0000 0.0122
-9.000 -0.7280 0.04039 0.03610 -0.0396 1.0000 0.0122
-8.750 -0.7297 0.03471 0.02979 -0.0402 1.0000 0.0124
-8.500 -0.7208 0.03066 0.02517 -0.0399 1.0000 0.0126
-8.250 -0.7060 0.02765 0.02166 -0.0393 1.0000 0.0129
-8.000 -0.6884 0.02543 0.01915 -0.0387 1.0000 0.0133
-7.750 -0.6680 0.02394 0.01750 -0.0381 1.0000 0.0139
-7.500 -0.6467 0.02258 0.01595 -0.0375 1.0000 0.0146
-7.250 -0.6249 0.02122 0.01438 -0.0368 1.0000 0.0155
-7.000 -0.6024 0.02001 0.01293 -0.0360 1.0000 0.0168
-6.750 -0.5798 0.01906 0.01190 -0.0354 1.0000 0.0185
-6.500 -0.5566 0.01824 0.01097 -0.0347 1.0000 0.0204
-6.250 -0.5334 0.01724 0.00981 -0.0339 1.0000 0.0225
-6.000 -0.5103 0.01643 0.00897 -0.0332 1.0000 0.0250
-5.750 -0.4863 0.01587 0.00830 -0.0325 1.0000 0.0288
-5.500 -0.4626 0.01524 0.00767 -0.0319 1.0000 0.0331
-5.250 -0.4383 0.01478 0.00712 -0.0312 1.0000 0.0383
-5.000 -0.4144 0.01427 0.00663 -0.0306 1.0000 0.0441
-4.750 -0.3903 0.01378 0.00609 -0.0299 1.0000 0.0500
-4.500 -0.3663 0.01333 0.00563 -0.0292 1.0000 0.0563
-4.250 -0.3423 0.01291 0.00519 -0.0285 1.0000 0.0637
-4.000 -0.3182 0.01258 0.00482 -0.0278 1.0000 0.0718
-3.750 -0.2944 0.01220 0.00449 -0.0271 1.0000 0.0816
-3.500 -0.2635 0.01186 0.00416 -0.0279 0.9965 0.0951
-3.250 -0.2260 0.01150 0.00385 -0.0300 0.9887 0.1145
-3.000 -0.1888 0.01112 0.00359 -0.0321 0.9802 0.1440
-2.500 -0.1175 0.01031 0.00314 -0.0356 0.9577 0.2390
-2.250 -0.0826 0.00992 0.00296 -0.0372 0.9435 0.3011
-2.000 -0.0474 0.00952 0.00280 -0.0387 0.9273 0.3713
-1.750 -0.0139 0.00912 0.00266 -0.0398 0.9071 0.4545
-1.500 0.0181 0.00874 0.00258 -0.0404 0.8843 0.5443
-1.250 0.0467 0.00845 0.00254 -0.0400 0.8581 0.6292
-1.000 0.0730 0.00828 0.00251 -0.0390 0.8306 0.6986
-0.750 0.0977 0.00820 0.00248 -0.0376 0.8025 0.7531
-0.500 0.1216 0.00818 0.00246 -0.0361 0.7744 0.7981
-0.250 0.1451 0.00818 0.00242 -0.0345 0.7470 0.8385
0.250 0.1966 0.00826 0.00235 -0.0323 0.6914 0.9105
0.500 0.2288 0.00832 0.00229 -0.0327 0.6623 0.9437
0.750 0.2660 0.00842 0.00223 -0.0344 0.6318 0.9750
1.000 0.3003 0.00854 0.00219 -0.0357 0.6021 1.0000
1.250 0.3253 0.00871 0.00221 -0.0351 0.5747 1.0000
1.500 0.3507 0.00889 0.00224 -0.0345 0.5479 1.0000
1.750 0.3764 0.00908 0.00229 -0.0340 0.5216 1.0000
2.000 0.4021 0.00929 0.00236 -0.0335 0.4957 1.0000
2.250 0.4281 0.00950 0.00245 -0.0331 0.4701 1.0000
2.500 0.4542 0.00972 0.00255 -0.0327 0.4446 1.0000
2.750 0.4803 0.00995 0.00267 -0.0323 0.4199 1.0000
3.000 0.5064 0.01020 0.00282 -0.0320 0.3954 1.0000
3.250 0.5326 0.01044 0.00297 -0.0316 0.3714 1.0000
3.500 0.5587 0.01071 0.00314 -0.0313 0.3484 1.0000
3.750 0.5849 0.01098 0.00335 -0.0310 0.3254 1.0000
4.000 0.6110 0.01128 0.00356 -0.0307 0.3039 1.0000
4.250 0.6371 0.01157 0.00379 -0.0304 0.2826 1.0000
4.750 0.6891 0.01222 0.00434 -0.0298 0.2434 1.0000
5.000 0.7150 0.01256 0.00463 -0.0294 0.2248 1.0000
5.250 0.7407 0.01293 0.00495 -0.0291 0.2071 1.0000
5.500 0.7663 0.01332 0.00531 -0.0288 0.1904 1.0000
5.750 0.7920 0.01370 0.00568 -0.0285 0.1748 1.0000
6.000 0.8174 0.01411 0.00608 -0.0281 0.1600 1.0000
6.250 0.8427 0.01454 0.00650 -0.0278 0.1462 1.0000
6.500 0.8678 0.01500 0.00697 -0.0274 0.1333 1.0000
7.000 0.9175 0.01596 0.00796 -0.0266 0.1100 1.0000
7.250 0.9421 0.01648 0.00849 -0.0262 0.0987 1.0000
7.500 0.9663 0.01702 0.00905 -0.0258 0.0872 1.0000
7.750 0.9902 0.01761 0.00967 -0.0253 0.0763 1.0000
8.000 1.0137 0.01824 0.01031 -0.0248 0.0668 1.0000
8.250 1.0366 0.01895 0.01101 -0.0243 0.0580 1.0000
8.500 1.0597 0.01960 0.01175 -0.0237 0.0501 1.0000
8.750 1.0819 0.02038 0.01261 -0.0231 0.0436 1.0000
9.000 1.1028 0.02131 0.01356 -0.0224 0.0379 1.0000
9.250 1.1239 0.02219 0.01458 -0.0216 0.0336 1.0000
9.500 1.1432 0.02325 0.01569 -0.0207 0.0300 1.0000
9.750 1.1620 0.02433 0.01691 -0.0198 0.0272 1.0000
10.000 1.1806 0.02537 0.01807 -0.0188 0.0248 1.0000
10.250 1.1969 0.02661 0.01943 -0.0177 0.0231 1.0000
10.500 1.2100 0.02812 0.02105 -0.0164 0.0220 1.0000
10.750 1.2242 0.02948 0.02259 -0.0151 0.0210 1.0000
11.000 1.2363 0.03093 0.02422 -0.0136 0.0201 1.0000
11.250 1.2469 0.03241 0.02585 -0.0121 0.0192 1.0000
11.500 1.2547 0.03390 0.02748 -0.0104 0.0184 1.0000
11.750 1.2582 0.03546 0.02916 -0.0084 0.0178 1.0000
12.000 1.2572 0.03744 0.03124 -0.0065 0.0172 1.0000
12.250 1.2526 0.03998 0.03390 -0.0051 0.0168 1.0000
12.500 1.2503 0.04259 0.03671 -0.0044 0.0165 1.0000
12.750 1.2468 0.04562 0.03994 -0.0045 0.0162 1.0000
13.000 1.2415 0.04915 0.04368 -0.0053 0.0160 1.0000
13.250 1.2345 0.05325 0.04798 -0.0067 0.0158 1.0000
13.500 1.2264 0.05782 0.05275 -0.0089 0.0156 1.0000
13.750 1.2163 0.06303 0.05815 -0.0116 0.0155 1.0000
14.000 1.2042 0.06886 0.06417 -0.0150 0.0153 1.0000
14.250 1.1905 0.07527 0.07077 -0.0188 0.0152 1.0000
14.500 1.1751 0.08228 0.07795 -0.0231 0.0151 1.0000
14.750 1.1577 0.08993 0.08578 -0.0278 0.0151 1.0000
15.000 1.1376 0.09846 0.09447 -0.0330 0.0151 1.0000
15.250 1.1164 0.10772 0.10390 -0.0388 0.0152 1.0000
15.500 1.0923 0.11814 0.11448 -0.0451 0.0154 1.0000
15.750 1.0653 0.12994 0.12641 -0.0523 0.0156 1.0000
16.000 1.0269 0.14577 0.14238 -0.0618 0.0160 1.0000
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Polar data table (+)
Polar graphs
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