SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 200,000 Max Cl/Cd: 57.87 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8000-il-200000-n5.txt Download as CSV file: xf-sd8000-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD8000-089-88
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5481 0.09987 0.09615 -0.0153 1.0000 0.0140
-10.500 -0.6987 0.05719 0.05346 -0.0418 1.0000 0.0122
-10.250 -0.7218 0.04884 0.04495 -0.0506 1.0000 0.0121
-10.000 -0.7403 0.04416 0.04004 -0.0524 1.0000 0.0120
-9.750 -0.7521 0.03929 0.03475 -0.0531 1.0000 0.0121
-9.500 -0.7537 0.03532 0.03034 -0.0527 1.0000 0.0122
-9.250 -0.7477 0.03236 0.02708 -0.0519 1.0000 0.0125
-9.000 -0.7360 0.03036 0.02489 -0.0509 1.0000 0.0128
-8.750 -0.7229 0.02850 0.02281 -0.0498 1.0000 0.0132
-8.500 -0.7085 0.02683 0.02091 -0.0485 1.0000 0.0137
-8.250 -0.6934 0.02520 0.01901 -0.0471 1.0000 0.0144
-8.000 -0.6775 0.02362 0.01717 -0.0457 1.0000 0.0151
-7.750 -0.6601 0.02233 0.01560 -0.0443 1.0000 0.0163
-7.500 -0.6425 0.02138 0.01461 -0.0430 1.0000 0.0175
-7.250 -0.6238 0.02053 0.01364 -0.0417 1.0000 0.0189
-7.000 -0.6052 0.01949 0.01241 -0.0403 1.0000 0.0203
-6.750 -0.5864 0.01846 0.01127 -0.0390 1.0000 0.0220
-6.500 -0.5664 0.01779 0.01052 -0.0379 1.0000 0.0241
-6.250 -0.5456 0.01723 0.00982 -0.0367 1.0000 0.0271
-6.000 -0.5143 0.01651 0.00907 -0.0379 0.9969 0.0311
-5.750 -0.4812 0.01597 0.00841 -0.0393 0.9937 0.0359
-5.500 -0.4493 0.01539 0.00780 -0.0404 0.9899 0.0414
-5.250 -0.4162 0.01484 0.00718 -0.0417 0.9864 0.0474
-5.000 -0.3816 0.01437 0.00666 -0.0433 0.9835 0.0541
-4.750 -0.3507 0.01390 0.00619 -0.0442 0.9788 0.0619
-4.500 -0.3173 0.01351 0.00573 -0.0454 0.9749 0.0707
-4.250 -0.2821 0.01316 0.00536 -0.0471 0.9718 0.0823
-4.000 -0.2499 0.01281 0.00503 -0.0481 0.9672 0.0957
-3.750 -0.2170 0.01245 0.00470 -0.0493 0.9625 0.1116
-3.500 -0.1821 0.01210 0.00442 -0.0509 0.9587 0.1333
-3.250 -0.1502 0.01177 0.00418 -0.0518 0.9534 0.1592
-3.000 -0.1189 0.01144 0.00395 -0.0526 0.9473 0.1934
-2.750 -0.0849 0.01109 0.00374 -0.0539 0.9429 0.2364
-2.500 -0.0572 0.01077 0.00359 -0.0539 0.9349 0.2851
-2.250 -0.0257 0.01039 0.00342 -0.0547 0.9289 0.3468
-2.000 0.0013 0.01006 0.00332 -0.0545 0.9201 0.4108
-1.750 0.0310 0.00972 0.00321 -0.0547 0.9132 0.4827
-1.500 0.0565 0.00944 0.00316 -0.0540 0.9026 0.5478
-1.250 0.0830 0.00919 0.00310 -0.0533 0.8928 0.6094
-1.000 0.1096 0.00895 0.00304 -0.0526 0.8831 0.6675
-0.750 0.1342 0.00876 0.00301 -0.0513 0.8708 0.7221
-0.500 0.1586 0.00859 0.00298 -0.0500 0.8583 0.7735
-0.250 0.1830 0.00846 0.00294 -0.0486 0.8451 0.8208
0.000 0.2086 0.00835 0.00289 -0.0473 0.8307 0.8656
0.250 0.2385 0.00826 0.00281 -0.0470 0.8145 0.9085
0.500 0.2746 0.00820 0.00270 -0.0482 0.7961 0.9456
0.750 0.3136 0.00816 0.00260 -0.0502 0.7745 0.9767
1.000 0.3503 0.00817 0.00249 -0.0518 0.7503 1.0000
1.250 0.3745 0.00826 0.00245 -0.0508 0.7242 1.0000
1.500 0.3989 0.00838 0.00243 -0.0499 0.6956 1.0000
1.750 0.4233 0.00853 0.00244 -0.0490 0.6648 1.0000
2.000 0.4478 0.00872 0.00247 -0.0482 0.6323 1.0000
2.250 0.4723 0.00894 0.00253 -0.0473 0.5979 1.0000
2.500 0.4967 0.00919 0.00262 -0.0465 0.5619 1.0000
2.750 0.5211 0.00947 0.00273 -0.0458 0.5248 1.0000
3.000 0.5453 0.00978 0.00286 -0.0450 0.4864 1.0000
3.250 0.5696 0.01011 0.00303 -0.0443 0.4480 1.0000
3.500 0.5938 0.01047 0.00323 -0.0437 0.4106 1.0000
3.750 0.6183 0.01082 0.00344 -0.0431 0.3752 1.0000
4.000 0.6427 0.01120 0.00367 -0.0425 0.3417 1.0000
4.250 0.6672 0.01159 0.00394 -0.0419 0.3104 1.0000
4.500 0.6916 0.01199 0.00423 -0.0414 0.2805 1.0000
4.750 0.7162 0.01239 0.00453 -0.0409 0.2530 1.0000
5.000 0.7407 0.01280 0.00485 -0.0404 0.2270 1.0000
5.250 0.7651 0.01323 0.00521 -0.0399 0.2041 1.0000
5.500 0.7895 0.01367 0.00558 -0.0394 0.1826 1.0000
5.750 0.8137 0.01413 0.00598 -0.0389 0.1642 1.0000
6.000 0.8380 0.01458 0.00640 -0.0384 0.1474 1.0000
6.250 0.8622 0.01505 0.00686 -0.0378 0.1326 1.0000
6.500 0.8861 0.01554 0.00734 -0.0373 0.1195 1.0000
6.750 0.9098 0.01605 0.00784 -0.0367 0.1068 1.0000
7.000 0.9332 0.01660 0.00837 -0.0361 0.0949 1.0000
7.500 0.9795 0.01772 0.00950 -0.0349 0.0722 1.0000
7.750 1.0024 0.01829 0.01011 -0.0343 0.0633 1.0000
8.000 1.0247 0.01894 0.01078 -0.0335 0.0554 1.0000
8.500 1.0680 0.02035 0.01229 -0.0320 0.0416 1.0000
8.750 1.0879 0.02123 0.01319 -0.0310 0.0368 1.0000
9.000 1.1081 0.02206 0.01414 -0.0300 0.0328 1.0000
9.250 1.1257 0.02314 0.01524 -0.0288 0.0296 1.0000
9.500 1.1444 0.02406 0.01630 -0.0276 0.0270 1.0000
9.750 1.1623 0.02501 0.01736 -0.0264 0.0249 1.0000
10.000 1.1779 0.02613 0.01858 -0.0251 0.0233 1.0000
10.250 1.1906 0.02751 0.02005 -0.0233 0.0222 1.0000
10.500 1.2044 0.02875 0.02146 -0.0217 0.0214 1.0000
10.750 1.2165 0.03007 0.02294 -0.0200 0.0206 1.0000
11.000 1.2261 0.03141 0.02443 -0.0179 0.0197 1.0000
11.250 1.2340 0.03273 0.02588 -0.0158 0.0189 1.0000
11.500 1.2402 0.03413 0.02739 -0.0137 0.0183 1.0000
11.750 1.2442 0.03574 0.02913 -0.0117 0.0177 1.0000
12.000 1.2435 0.03793 0.03141 -0.0097 0.0171 1.0000
12.250 1.2458 0.03998 0.03365 -0.0081 0.0167 1.0000
12.500 1.2460 0.04231 0.03620 -0.0068 0.0164 1.0000
12.750 1.2442 0.04496 0.03907 -0.0059 0.0161 1.0000
13.000 1.2405 0.04796 0.04229 -0.0054 0.0158 1.0000
13.250 1.2350 0.05135 0.04588 -0.0054 0.0155 1.0000
13.500 1.2275 0.05523 0.04997 -0.0061 0.0153 1.0000
13.750 1.2183 0.05962 0.05457 -0.0075 0.0151 1.0000
14.000 1.2071 0.06467 0.05982 -0.0097 0.0149 1.0000
14.250 1.1945 0.07034 0.06569 -0.0127 0.0148 1.0000
14.500 1.1794 0.07687 0.07242 -0.0165 0.0147 1.0000
14.750 1.1606 0.08456 0.08032 -0.0212 0.0147 1.0000
15.000 1.1393 0.09330 0.08927 -0.0267 0.0148 1.0000
15.250 1.1140 0.10350 0.09967 -0.0332 0.0149 1.0000
15.500 1.0828 0.11578 0.11214 -0.0410 0.0152 1.0000
15.750 1.0417 0.13157 0.12811 -0.0507 0.0157 1.0000
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Polar data table (+)
Polar graphs
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