SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 500,000 Max Cl/Cd: 78.48 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7003-il-500000.txt Download as CSV file: xf-sd7003-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6418 0.07188 0.06968 -0.0177 1.0000 0.0135
-9.500 -0.6941 0.05165 0.04937 -0.0350 1.0000 0.0125
-9.250 -0.7245 0.04318 0.04055 -0.0399 1.0000 0.0123
-9.000 -0.7413 0.03550 0.03232 -0.0414 1.0000 0.0121
-8.750 -0.7418 0.02981 0.02603 -0.0413 1.0000 0.0121
-8.500 -0.7302 0.02634 0.02210 -0.0406 1.0000 0.0123
-8.250 -0.7138 0.02376 0.01914 -0.0398 1.0000 0.0125
-8.000 -0.6944 0.02188 0.01693 -0.0390 1.0000 0.0128
-7.750 -0.6732 0.02044 0.01524 -0.0382 1.0000 0.0130
-7.500 -0.6549 0.01799 0.01250 -0.0372 1.0000 0.0137
-7.250 -0.6325 0.01708 0.01155 -0.0365 1.0000 0.0145
-7.000 -0.6092 0.01633 0.01071 -0.0358 1.0000 0.0153
-6.750 -0.5861 0.01541 0.00967 -0.0350 1.0000 0.0162
-6.500 -0.5626 0.01461 0.00874 -0.0341 1.0000 0.0170
-6.250 -0.5405 0.01335 0.00737 -0.0332 1.0000 0.0184
-6.000 -0.5167 0.01275 0.00676 -0.0325 1.0000 0.0202
-5.750 -0.4923 0.01229 0.00623 -0.0317 1.0000 0.0224
-5.500 -0.4689 0.01155 0.00548 -0.0309 1.0000 0.0260
-5.250 -0.4443 0.01135 0.00524 -0.0302 1.0000 0.0296
-5.000 -0.4206 0.01074 0.00465 -0.0294 1.0000 0.0352
-4.750 -0.3965 0.01035 0.00424 -0.0287 1.0000 0.0406
-4.500 -0.3722 0.01011 0.00401 -0.0280 1.0000 0.0472
-4.250 -0.3484 0.00975 0.00368 -0.0272 1.0000 0.0551
-4.000 -0.3245 0.00953 0.00344 -0.0264 1.0000 0.0625
-3.750 -0.2945 0.00927 0.00321 -0.0269 0.9986 0.0725
-3.500 -0.2544 0.00896 0.00293 -0.0296 0.9945 0.0860
-3.250 -0.2161 0.00861 0.00267 -0.0318 0.9894 0.1052
-3.000 -0.1762 0.00825 0.00246 -0.0344 0.9845 0.1382
-2.750 -0.1391 0.00782 0.00225 -0.0365 0.9776 0.1922
-2.250 -0.0660 0.00699 0.00193 -0.0403 0.9591 0.3343
-2.000 -0.0316 0.00660 0.00179 -0.0416 0.9447 0.4101
-1.750 0.0011 0.00621 0.00167 -0.0425 0.9259 0.4967
-1.500 0.0298 0.00591 0.00159 -0.0424 0.9005 0.5785
-1.250 0.0560 0.00573 0.00153 -0.0416 0.8718 0.6460
-1.000 0.0810 0.00563 0.00151 -0.0406 0.8421 0.7060
-0.750 0.1056 0.00559 0.00151 -0.0394 0.8125 0.7551
-0.500 0.1301 0.00558 0.00150 -0.0382 0.7833 0.7977
-0.250 0.1542 0.00559 0.00151 -0.0370 0.7548 0.8363
0.000 0.1779 0.00562 0.00151 -0.0356 0.7270 0.8710
0.250 0.2010 0.00566 0.00151 -0.0340 0.6998 0.9040
0.500 0.2254 0.00571 0.00150 -0.0328 0.6727 0.9370
0.750 0.2579 0.00579 0.00147 -0.0334 0.6439 0.9669
1.000 0.2973 0.00590 0.00144 -0.0358 0.6127 0.9900
1.250 0.3290 0.00604 0.00144 -0.0366 0.5837 1.0000
1.500 0.3546 0.00620 0.00146 -0.0361 0.5562 1.0000
1.750 0.3808 0.00637 0.00150 -0.0357 0.5287 1.0000
2.000 0.4072 0.00654 0.00156 -0.0353 0.5018 1.0000
2.250 0.4338 0.00673 0.00163 -0.0350 0.4755 1.0000
2.500 0.4605 0.00692 0.00170 -0.0347 0.4496 1.0000
3.000 0.5140 0.00733 0.00191 -0.0342 0.3985 1.0000
3.250 0.5409 0.00754 0.00202 -0.0340 0.3740 1.0000
3.500 0.5676 0.00778 0.00215 -0.0338 0.3503 1.0000
3.750 0.5945 0.00800 0.00229 -0.0336 0.3261 1.0000
4.000 0.6212 0.00825 0.00246 -0.0333 0.3041 1.0000
4.250 0.6479 0.00851 0.00263 -0.0331 0.2813 1.0000
4.500 0.6746 0.00878 0.00282 -0.0329 0.2600 1.0000
4.750 0.7012 0.00906 0.00303 -0.0327 0.2387 1.0000
5.000 0.7276 0.00936 0.00325 -0.0324 0.2197 1.0000
5.250 0.7541 0.00964 0.00349 -0.0322 0.2013 1.0000
5.500 0.7805 0.00995 0.00374 -0.0319 0.1839 1.0000
5.750 0.8068 0.01028 0.00402 -0.0317 0.1682 1.0000
6.000 0.8329 0.01062 0.00431 -0.0314 0.1527 1.0000
6.250 0.8589 0.01098 0.00462 -0.0311 0.1381 1.0000
6.500 0.8847 0.01136 0.00496 -0.0308 0.1228 1.0000
6.750 0.9104 0.01175 0.00530 -0.0305 0.1089 1.0000
7.000 0.9361 0.01213 0.00566 -0.0302 0.0975 1.0000
7.250 0.9617 0.01252 0.00604 -0.0299 0.0870 1.0000
7.500 0.9871 0.01294 0.00647 -0.0296 0.0775 1.0000
7.750 1.0120 0.01341 0.00693 -0.0292 0.0680 1.0000
8.000 1.0364 0.01395 0.00743 -0.0287 0.0581 1.0000
8.250 1.0609 0.01446 0.00793 -0.0283 0.0492 1.0000
8.500 1.0849 0.01505 0.00852 -0.0278 0.0409 1.0000
8.750 1.1080 0.01577 0.00928 -0.0272 0.0336 1.0000
9.000 1.1294 0.01672 0.01025 -0.0264 0.0283 1.0000
9.250 1.1526 0.01736 0.01096 -0.0257 0.0254 1.0000
9.500 1.1712 0.01861 0.01225 -0.0247 0.0224 1.0000
9.750 1.1933 0.01934 0.01309 -0.0239 0.0212 1.0000
10.000 1.2142 0.02016 0.01401 -0.0231 0.0200 1.0000
10.250 1.2342 0.02106 0.01500 -0.0222 0.0189 1.0000
10.500 1.2518 0.02218 0.01619 -0.0211 0.0178 1.0000
10.750 1.2621 0.02414 0.01829 -0.0192 0.0167 1.0000
11.000 1.2807 0.02500 0.01927 -0.0182 0.0162 1.0000
11.250 1.2964 0.02613 0.02053 -0.0169 0.0156 1.0000
11.500 1.3102 0.02735 0.02188 -0.0155 0.0150 1.0000
11.750 1.3219 0.02866 0.02332 -0.0139 0.0145 1.0000
12.000 1.3313 0.02995 0.02472 -0.0122 0.0139 1.0000
12.250 1.3353 0.03130 0.02615 -0.0097 0.0135 1.0000
12.500 1.3335 0.03313 0.02809 -0.0072 0.0132 1.0000
12.750 1.3262 0.03569 0.03079 -0.0050 0.0129 1.0000
13.000 1.3094 0.03968 0.03497 -0.0036 0.0125 1.0000
13.250 1.3086 0.04217 0.03763 -0.0036 0.0123 1.0000
13.500 1.3049 0.04534 0.04097 -0.0041 0.0122 1.0000
13.750 1.3006 0.04890 0.04469 -0.0054 0.0120 1.0000
14.000 1.2943 0.05306 0.04901 -0.0073 0.0118 1.0000
14.250 1.2839 0.05815 0.05428 -0.0098 0.0117 1.0000
14.500 1.2722 0.06376 0.06005 -0.0129 0.0116 1.0000
14.750 1.2593 0.06983 0.06629 -0.0165 0.0116 1.0000
15.000 1.2469 0.07615 0.07275 -0.0204 0.0114 1.0000
15.250 1.2294 0.08354 0.08031 -0.0248 0.0114 1.0000
15.500 1.2099 0.09163 0.08855 -0.0297 0.0115 1.0000
15.750 1.1906 0.10012 0.09719 -0.0349 0.0115 1.0000
16.000 1.1708 0.10913 0.10635 -0.0405 0.0115 1.0000
16.250 1.1476 0.11929 0.11666 -0.0468 0.0117 1.0000
16.500 1.1234 0.13025 0.12777 -0.0535 0.0118 1.0000
16.750 1.0948 0.14289 0.14056 -0.0613 0.0120 1.0000
17.000 1.0458 0.16227 0.16008 -0.0730 0.0124 1.0000
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Polar data table (+)
Polar graphs
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