Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 500,000 Max Cl/Cd: 63.73 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-500000.txt Download as CSV file: xf-supermarine371ii-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-II (tip)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5465 0.08411 0.08200 -0.0250 1.0000 0.0092
-8.750 -0.5473 0.07934 0.07726 -0.0296 1.0000 0.0091
-8.500 -0.5587 0.07436 0.07228 -0.0331 1.0000 0.0092
-8.250 -0.5671 0.07057 0.06846 -0.0339 1.0000 0.0093
-8.000 -0.5695 0.06641 0.06424 -0.0351 1.0000 0.0093
-7.750 -0.5710 0.06227 0.06003 -0.0357 1.0000 0.0095
-7.500 -0.5690 0.05881 0.05651 -0.0360 1.0000 0.0098
-7.250 -0.5562 0.05456 0.05214 -0.0382 0.9828 0.0101
-7.000 -0.5344 0.04996 0.04735 -0.0418 0.9642 0.0107
-6.750 -0.5169 0.04610 0.04327 -0.0432 0.9461 0.0116
-6.500 -0.5043 0.04275 0.03967 -0.0423 0.9303 0.0127
-6.250 -0.4758 0.04208 0.03874 -0.0406 0.9194 0.0161
-6.000 -0.4612 0.03934 0.03571 -0.0390 0.9092 0.0163
-5.750 -0.4462 0.03662 0.03266 -0.0373 0.9007 0.0164
-5.500 -0.4430 0.02905 0.02458 -0.0353 0.8919 0.0177
-5.250 -0.4247 0.02660 0.02189 -0.0346 0.8858 0.0188
-5.000 -0.4036 0.02460 0.01968 -0.0338 0.8798 0.0199
-4.750 -0.3814 0.02265 0.01745 -0.0328 0.8751 0.0212
-4.500 -0.3571 0.02055 0.01506 -0.0319 0.8699 0.0221
-4.250 -0.3294 0.01682 0.01082 -0.0299 0.8657 0.0144
-4.000 -0.3037 0.01478 0.00850 -0.0289 0.8621 0.0145
-3.750 -0.2773 0.01372 0.00730 -0.0284 0.8580 0.0158
-3.500 -0.2538 0.01214 0.00559 -0.0275 0.8539 0.0182
-3.250 -0.2301 0.01126 0.00460 -0.0268 0.8503 0.0207
-3.000 -0.2055 0.01064 0.00390 -0.0262 0.8468 0.0235
-2.750 -0.1799 0.01020 0.00339 -0.0259 0.8430 0.0262
-2.500 -0.1544 0.00974 0.00284 -0.0255 0.8396 0.0301
-2.250 -0.1292 0.00921 0.00237 -0.0250 0.8367 0.0645
-2.000 -0.1207 0.00668 0.00197 -0.0227 0.8334 0.6505
-1.750 -0.0972 0.00644 0.00199 -0.0217 0.8303 0.7381
-1.500 -0.0727 0.00653 0.00216 -0.0207 0.8274 0.7944
-1.250 -0.0479 0.00659 0.00223 -0.0198 0.8247 0.8212
-1.000 -0.0233 0.00664 0.00231 -0.0188 0.8223 0.8415
-0.750 0.0025 0.00668 0.00236 -0.0182 0.8200 0.8542
-0.500 0.0292 0.00670 0.00238 -0.0180 0.8175 0.8636
-0.250 0.0570 0.00670 0.00237 -0.0181 0.8150 0.8682
0.000 0.0849 0.00671 0.00236 -0.0184 0.8127 0.8732
0.250 0.1126 0.00671 0.00236 -0.0185 0.8105 0.8773
0.500 0.1403 0.00674 0.00239 -0.0186 0.8086 0.8822
0.750 0.1681 0.00678 0.00244 -0.0187 0.8066 0.8879
1.000 0.1955 0.00679 0.00251 -0.0188 0.8041 0.8927
1.250 0.2230 0.00682 0.00258 -0.0189 0.8017 0.8985
1.500 0.2502 0.00682 0.00263 -0.0189 0.7983 0.9039
1.750 0.2768 0.00681 0.00264 -0.0185 0.7928 0.9096
2.000 0.3026 0.00670 0.00256 -0.0179 0.7816 0.9158
2.250 0.3265 0.00646 0.00232 -0.0166 0.7585 0.9222
2.500 0.3508 0.00628 0.00211 -0.0155 0.7307 0.9294
2.750 0.3760 0.00620 0.00204 -0.0147 0.7015 0.9361
3.000 0.3996 0.00627 0.00196 -0.0136 0.6222 0.9439
3.250 0.4020 0.00913 0.00275 -0.0103 0.1110 0.9578
3.500 0.4280 0.01012 0.00343 -0.0104 0.0304 0.9670
3.750 0.4607 0.01065 0.00404 -0.0117 0.0247 0.9732
4.000 0.4906 0.01169 0.00518 -0.0126 0.0191 0.9812
4.250 0.5240 0.01256 0.00613 -0.0141 0.0166 0.9867
4.500 0.5554 0.01391 0.00757 -0.0151 0.0151 0.9932
4.750 0.5880 0.01547 0.00928 -0.0161 0.0145 0.9991
5.000 0.6071 0.01608 0.00990 -0.0150 0.0125 1.0000
5.250 0.6272 0.01892 0.01292 -0.0134 0.0114 1.0000
5.500 0.6484 0.02212 0.01645 -0.0118 0.0112 1.0000
5.750 0.6728 0.02647 0.02143 -0.0086 0.0171 1.0000
6.000 0.6926 0.02903 0.02428 -0.0069 0.0162 1.0000
6.250 0.7108 0.03169 0.02722 -0.0052 0.0151 1.0000
6.500 0.7272 0.03442 0.03021 -0.0035 0.0141 1.0000
6.750 0.7419 0.03719 0.03322 -0.0020 0.0134 1.0000
7.000 0.7548 0.04007 0.03630 -0.0005 0.0129 1.0000
7.250 0.7654 0.04297 0.03938 0.0009 0.0124 1.0000
7.500 0.7741 0.04606 0.04268 0.0023 0.0121 1.0000
7.750 0.7764 0.05007 0.04688 0.0039 0.0117 1.0000
8.000 0.7733 0.05483 0.05185 0.0057 0.0114 1.0000
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Polar data table (+)
Polar graphs
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