RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 200,000 Max Cl/Cd: 48.85 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil2-il-200000.txt Download as CSV file: xf-amsoil2-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5756 0.10139 0.09749 -0.0157 1.0000 0.0815
-10.000 -0.4901 0.08483 0.08117 -0.0330 1.0000 0.0897
-9.750 -0.7849 0.05759 0.05273 -0.0432 1.0000 0.0608
-9.500 -0.7690 0.05464 0.04980 -0.0430 1.0000 0.0599
-9.250 -0.7677 0.05052 0.04551 -0.0422 1.0000 0.0594
-9.000 -0.7706 0.04579 0.04044 -0.0408 1.0000 0.0591
-8.750 -0.7724 0.04136 0.03559 -0.0387 1.0000 0.0590
-8.500 -0.7726 0.03798 0.03184 -0.0357 1.0000 0.0592
-8.250 -0.7728 0.03527 0.02877 -0.0321 1.0000 0.0594
-8.000 -0.7710 0.03298 0.02610 -0.0285 1.0000 0.0599
-7.750 -0.7659 0.03103 0.02375 -0.0253 1.0000 0.0608
-7.500 -0.7534 0.02956 0.02230 -0.0235 1.0000 0.0620
-7.250 -0.7387 0.02884 0.02161 -0.0218 1.0000 0.0632
-7.000 -0.7111 0.02743 0.02002 -0.0225 0.9978 0.0649
-6.750 -0.6768 0.02572 0.01798 -0.0243 0.9947 0.0668
-6.500 -0.6433 0.02427 0.01619 -0.0259 0.9914 0.0691
-6.250 -0.6095 0.02307 0.01504 -0.0277 0.9880 0.0714
-6.000 -0.5731 0.02214 0.01403 -0.0297 0.9850 0.0739
-5.750 -0.5359 0.02135 0.01305 -0.0318 0.9822 0.0771
-5.500 -0.5036 0.02022 0.01193 -0.0330 0.9779 0.0802
-5.250 -0.4680 0.01953 0.01126 -0.0349 0.9745 0.0837
-5.000 -0.4299 0.01898 0.01059 -0.0370 0.9720 0.0880
-4.750 -0.3945 0.01805 0.00977 -0.0389 0.9693 0.0930
-4.500 -0.3620 0.01756 0.00927 -0.0400 0.9642 0.0985
-4.250 -0.3259 0.01681 0.00861 -0.0420 0.9610 0.1055
-4.000 -0.2882 0.01632 0.00811 -0.0441 0.9583 0.1142
-3.750 -0.2570 0.01578 0.00769 -0.0451 0.9536 0.1240
-3.500 -0.2267 0.01529 0.00729 -0.0458 0.9481 0.1356
-3.250 -0.1929 0.01479 0.00689 -0.0472 0.9442 0.1515
-3.000 -0.1629 0.01436 0.00658 -0.0478 0.9394 0.1732
-2.750 -0.1372 0.01384 0.00629 -0.0477 0.9329 0.2117
-2.500 -0.1164 0.01201 0.00590 -0.0475 0.9282 0.5026
-2.250 -0.0959 0.01168 0.00629 -0.0453 0.9225 0.6882
-2.000 -0.0719 0.01181 0.00653 -0.0439 0.9160 0.7379
-1.750 -0.0448 0.01195 0.00670 -0.0429 0.9116 0.7698
-1.500 -0.0202 0.01216 0.00695 -0.0416 0.9067 0.7942
-1.250 0.0024 0.01238 0.00719 -0.0399 0.8999 0.8155
-1.000 0.0265 0.01254 0.00736 -0.0382 0.8950 0.8345
-0.750 0.0501 0.01271 0.00755 -0.0364 0.8907 0.8506
-0.500 0.0710 0.01292 0.00779 -0.0346 0.8836 0.8655
-0.250 0.0936 0.01302 0.00790 -0.0327 0.8783 0.8801
0.000 0.1165 0.01311 0.00798 -0.0307 0.8744 0.8949
0.250 0.1353 0.01328 0.00819 -0.0283 0.8664 0.9110
0.500 0.1569 0.01317 0.00808 -0.0254 0.8588 0.9274
0.750 0.1832 0.01302 0.00792 -0.0239 0.8478 0.9394
1.000 0.2134 0.01264 0.00750 -0.0231 0.8386 0.9458
1.250 0.2440 0.01241 0.00725 -0.0231 0.8256 0.9525
1.500 0.2755 0.01213 0.00696 -0.0231 0.8144 0.9590
1.750 0.3118 0.01185 0.00664 -0.0241 0.8029 0.9639
2.000 0.3446 0.01163 0.00642 -0.0247 0.7885 0.9709
2.250 0.3841 0.01133 0.00610 -0.0264 0.7706 0.9746
2.500 0.4206 0.01104 0.00576 -0.0276 0.7493 0.9796
2.750 0.4569 0.01083 0.00554 -0.0289 0.7215 0.9847
3.000 0.4945 0.01066 0.00528 -0.0305 0.6805 0.9896
3.250 0.5276 0.01080 0.00496 -0.0311 0.5607 0.9951
3.500 0.5463 0.01339 0.00565 -0.0311 0.2132 1.0000
3.750 0.5602 0.01408 0.00605 -0.0293 0.1743 1.0000
4.000 0.5743 0.01455 0.00639 -0.0272 0.1548 1.0000
4.250 0.5870 0.01503 0.00676 -0.0249 0.1420 1.0000
4.500 0.6014 0.01539 0.00707 -0.0227 0.1319 1.0000
4.750 0.6176 0.01590 0.00751 -0.0208 0.1235 1.0000
5.000 0.6380 0.01645 0.00797 -0.0198 0.1160 1.0000
5.250 0.6605 0.01706 0.00856 -0.0190 0.1093 1.0000
5.500 0.6841 0.01763 0.00905 -0.0185 0.1033 1.0000
5.750 0.7079 0.01843 0.00980 -0.0179 0.0983 1.0000
6.000 0.7328 0.01902 0.01038 -0.0176 0.0936 1.0000
6.250 0.7573 0.02003 0.01124 -0.0173 0.0893 1.0000
6.500 0.7829 0.02066 0.01196 -0.0169 0.0859 1.0000
6.750 0.8084 0.02136 0.01268 -0.0166 0.0824 1.0000
7.000 0.8340 0.02232 0.01353 -0.0165 0.0793 1.0000
7.250 0.8597 0.02333 0.01464 -0.0162 0.0766 1.0000
7.500 0.8852 0.02421 0.01562 -0.0158 0.0739 1.0000
7.750 0.9102 0.02505 0.01646 -0.0156 0.0714 1.0000
8.000 0.9365 0.02665 0.01797 -0.0157 0.0690 1.0000
8.250 0.9596 0.02766 0.01926 -0.0149 0.0671 1.0000
8.500 0.9831 0.02887 0.02064 -0.0144 0.0650 1.0000
8.750 1.0067 0.02986 0.02167 -0.0140 0.0631 1.0000
9.000 1.0308 0.03128 0.02303 -0.0139 0.0613 1.0000
9.250 1.0495 0.03327 0.02536 -0.0128 0.0599 1.0000
9.500 1.0663 0.03538 0.02785 -0.0114 0.0585 1.0000
9.750 1.0823 0.03743 0.03020 -0.0101 0.0571 1.0000
10.000 1.1001 0.03892 0.03181 -0.0092 0.0557 1.0000
10.250 1.1221 0.03992 0.03273 -0.0089 0.0544 1.0000
10.500 1.1361 0.04287 0.03579 -0.0080 0.0534 1.0000
10.750 1.1354 0.04615 0.03961 -0.0051 0.0529 1.0000
11.000 1.1298 0.05009 0.04403 -0.0021 0.0526 1.0000
11.250 1.1188 0.05429 0.04862 0.0009 0.0525 1.0000
11.500 1.1017 0.05841 0.05306 0.0042 0.0525 1.0000
11.750 1.0799 0.06239 0.05730 0.0074 0.0526 1.0000
12.000 1.0565 0.06676 0.06189 0.0093 0.0528 1.0000
12.250 1.0335 0.07156 0.06687 0.0100 0.0530 1.0000
12.500 1.0119 0.07680 0.07225 0.0096 0.0532 1.0000
12.750 0.9943 0.08230 0.07785 0.0085 0.0534 1.0000
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Polar data table (+)
Polar graphs
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