S9037 (9%) (s9037-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 100,000 Max Cl/Cd: 57.66 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9037-il-100000-n5.txt Download as CSV file: xf-s9037-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9037 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3341 0.09143 0.08670 -0.0335 1.0000 0.0457
-7.750 -0.3362 0.08870 0.08406 -0.0336 1.0000 0.0452
-7.500 -0.3417 0.08614 0.08159 -0.0332 1.0000 0.0446
-7.000 -0.3712 0.07869 0.07434 -0.0341 1.0000 0.0269
-6.750 -0.3777 0.07638 0.07209 -0.0327 1.0000 0.0261
-6.500 -0.3845 0.07379 0.06956 -0.0321 1.0000 0.0253
-6.250 -0.3717 0.06884 0.06459 -0.0375 0.9954 0.0240
-6.000 -0.3372 0.05621 0.05158 -0.0532 0.9856 0.0200
-5.750 -0.3135 0.05127 0.04648 -0.0581 0.9785 0.0196
-5.500 -0.2851 0.04576 0.04069 -0.0636 0.9719 0.0191
-5.250 -0.2581 0.04072 0.03527 -0.0675 0.9644 0.0187
-5.000 -0.2263 0.03566 0.02966 -0.0714 0.9585 0.0185
-4.750 -0.1965 0.03159 0.02500 -0.0735 0.9517 0.0184
-4.500 -0.1636 0.02817 0.02091 -0.0754 0.9460 0.0186
-4.250 -0.1259 0.02562 0.01768 -0.0775 0.9423 0.0199
-4.000 -0.0988 0.02390 0.01576 -0.0779 0.9344 0.0220
-3.750 -0.0636 0.02232 0.01389 -0.0794 0.9297 0.0243
-3.500 -0.0335 0.02084 0.01214 -0.0795 0.9226 0.0260
-3.250 -0.0006 0.01944 0.01052 -0.0801 0.9168 0.0287
-3.000 0.0299 0.01858 0.00962 -0.0807 0.9097 0.0358
-2.750 0.0612 0.01765 0.00862 -0.0812 0.9026 0.0482
-2.500 0.0907 0.01677 0.00778 -0.0813 0.8948 0.0766
-2.250 0.1212 0.01585 0.00718 -0.0819 0.8875 0.1482
-2.000 0.1481 0.01514 0.00687 -0.0818 0.8783 0.2602
-1.750 0.1781 0.01436 0.00660 -0.0822 0.8715 0.4181
-1.500 0.1999 0.01365 0.00650 -0.0806 0.8612 0.6038
-1.250 0.2320 0.01285 0.00635 -0.0795 0.8546 0.8822
-1.000 0.2828 0.01265 0.00592 -0.0838 0.8464 1.0000
-0.750 0.3094 0.01266 0.00571 -0.0834 0.8355 1.0000
-0.500 0.3369 0.01265 0.00549 -0.0830 0.8251 1.0000
-0.250 0.3647 0.01263 0.00529 -0.0826 0.8148 1.0000
0.000 0.3904 0.01267 0.00517 -0.0820 0.8026 1.0000
0.250 0.4165 0.01271 0.00508 -0.0814 0.7905 1.0000
0.500 0.4429 0.01275 0.00498 -0.0808 0.7784 1.0000
0.750 0.4694 0.01280 0.00491 -0.0803 0.7661 1.0000
1.000 0.4959 0.01285 0.00485 -0.0798 0.7534 1.0000
1.250 0.5223 0.01290 0.00481 -0.0792 0.7401 1.0000
1.500 0.5486 0.01298 0.00478 -0.0786 0.7261 1.0000
1.750 0.5747 0.01306 0.00478 -0.0780 0.7116 1.0000
2.000 0.6007 0.01317 0.00481 -0.0774 0.6966 1.0000
2.250 0.6266 0.01328 0.00487 -0.0768 0.6811 1.0000
2.500 0.6524 0.01341 0.00493 -0.0762 0.6655 1.0000
2.750 0.6782 0.01356 0.00501 -0.0756 0.6495 1.0000
3.000 0.7039 0.01371 0.00510 -0.0749 0.6329 1.0000
3.250 0.7294 0.01389 0.00523 -0.0743 0.6157 1.0000
3.500 0.7544 0.01409 0.00539 -0.0736 0.5967 1.0000
3.750 0.7793 0.01430 0.00555 -0.0729 0.5776 1.0000
4.000 0.8042 0.01453 0.00572 -0.0722 0.5587 1.0000
4.250 0.8287 0.01479 0.00599 -0.0715 0.5390 1.0000
4.500 0.8531 0.01507 0.00623 -0.0707 0.5194 1.0000
4.750 0.8772 0.01537 0.00649 -0.0700 0.4991 1.0000
5.000 0.9009 0.01569 0.00679 -0.0692 0.4775 1.0000
5.250 0.9243 0.01605 0.00714 -0.0684 0.4562 1.0000
5.500 0.9474 0.01643 0.00749 -0.0675 0.4348 1.0000
5.750 0.9703 0.01684 0.00788 -0.0667 0.4140 1.0000
6.000 0.9929 0.01727 0.00831 -0.0658 0.3927 1.0000
6.250 1.0151 0.01774 0.00879 -0.0649 0.3721 1.0000
6.500 1.0368 0.01823 0.00929 -0.0639 0.3504 1.0000
6.750 1.0579 0.01876 0.00982 -0.0629 0.3288 1.0000
7.000 1.0785 0.01933 0.01038 -0.0618 0.3064 1.0000
7.250 1.0987 0.01993 0.01099 -0.0608 0.2844 1.0000
7.500 1.1181 0.02059 0.01167 -0.0596 0.2636 1.0000
7.750 1.1373 0.02127 0.01237 -0.0584 0.2432 1.0000
8.000 1.1558 0.02200 0.01313 -0.0572 0.2238 1.0000
8.250 1.1732 0.02280 0.01393 -0.0558 0.2050 1.0000
8.500 1.1905 0.02361 0.01479 -0.0545 0.1867 1.0000
8.750 1.2062 0.02451 0.01574 -0.0530 0.1693 1.0000
9.000 1.2206 0.02549 0.01672 -0.0514 0.1527 1.0000
9.250 1.2343 0.02649 0.01776 -0.0497 0.1377 1.0000
9.500 1.2471 0.02755 0.01887 -0.0480 0.1240 1.0000
9.750 1.2574 0.02868 0.02005 -0.0459 0.1123 1.0000
10.000 1.2669 0.02983 0.02129 -0.0438 0.1010 1.0000
10.250 1.2754 0.03108 0.02266 -0.0416 0.0914 1.0000
10.500 1.2812 0.03253 0.02416 -0.0394 0.0836 1.0000
10.750 1.2867 0.03405 0.02582 -0.0373 0.0758 1.0000
11.000 1.2919 0.03568 0.02758 -0.0354 0.0686 1.0000
11.250 1.2934 0.03760 0.02954 -0.0335 0.0630 1.0000
11.500 1.2971 0.03953 0.03165 -0.0319 0.0572 1.0000
11.750 1.2972 0.04173 0.03394 -0.0305 0.0522 1.0000
12.000 1.2977 0.04411 0.03648 -0.0292 0.0475 1.0000
12.250 1.2973 0.04661 0.03913 -0.0284 0.0428 1.0000
12.500 1.2921 0.04972 0.04229 -0.0278 0.0397 1.0000
12.750 1.2915 0.05261 0.04544 -0.0274 0.0356 1.0000
13.000 1.2866 0.05604 0.04899 -0.0276 0.0323 1.0000
13.250 1.2778 0.06011 0.05313 -0.0281 0.0302 1.0000
13.500 1.2732 0.06398 0.05727 -0.0287 0.0276 1.0000
13.750 1.2655 0.06839 0.06186 -0.0299 0.0255 1.0000
14.000 1.2566 0.07315 0.06676 -0.0315 0.0242 1.0000
14.250 1.2449 0.07856 0.07229 -0.0336 0.0230 1.0000
14.500 1.2333 0.08414 0.07797 -0.0357 0.0222 1.0000
14.750 1.2237 0.08982 0.08390 -0.0380 0.0212 1.0000
15.000 1.2127 0.09596 0.09027 -0.0408 0.0203 1.0000
15.250 1.2015 0.10233 0.09684 -0.0439 0.0196 1.0000
15.500 1.1895 0.10910 0.10379 -0.0474 0.0191 1.0000
15.750 1.1769 0.11625 0.11111 -0.0512 0.0186 1.0000
16.000 1.1642 0.12369 0.11872 -0.0553 0.0183 1.0000
16.250 1.1512 0.13148 0.12667 -0.0598 0.0180 1.0000
16.500 1.1368 0.13994 0.13529 -0.0646 0.0181 1.0000
16.750 1.1197 0.14963 0.14516 -0.0703 0.0184 1.0000
17.000 1.0970 0.16167 0.15736 -0.0773 0.0193 1.0000
17.250 1.0718 0.17559 0.17134 -0.0852 0.0203 1.0000
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Polar data table (+)
Polar graphs
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