HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 500,000 Max Cl/Cd: 76.11 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest3-il-500000.txt Download as CSV file: xf-tempest3-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.4232 0.14199 0.13970 -0.0167 1.0000 0.0158
-13.750 -0.4224 0.13882 0.13653 -0.0182 1.0000 0.0158
-7.500 -0.7292 0.03433 0.03050 -0.0155 1.0000 0.0150
-7.250 -0.7175 0.02858 0.02416 -0.0146 0.9969 0.0141
-7.000 -0.6921 0.02530 0.02043 -0.0150 0.9943 0.0142
-6.750 -0.6666 0.02291 0.01767 -0.0150 0.9910 0.0145
-6.500 -0.6392 0.02038 0.01478 -0.0152 0.9880 0.0145
-6.250 -0.6086 0.01844 0.01257 -0.0159 0.9856 0.0147
-6.000 -0.5752 0.01718 0.01113 -0.0172 0.9837 0.0153
-5.750 -0.5407 0.01620 0.01001 -0.0187 0.9821 0.0159
-5.500 -0.5190 0.01426 0.00789 -0.0177 0.9769 0.0171
-5.250 -0.4876 0.01350 0.00710 -0.0188 0.9737 0.0190
-5.000 -0.4537 0.01283 0.00638 -0.0203 0.9714 0.0212
-4.750 -0.4183 0.01226 0.00573 -0.0220 0.9697 0.0232
-4.500 -0.3927 0.01144 0.00485 -0.0216 0.9645 0.0286
-4.250 -0.3620 0.01078 0.00424 -0.0223 0.9608 0.0492
-4.000 -0.3292 0.01007 0.00385 -0.0238 0.9583 0.1159
-3.750 -0.2935 0.00959 0.00355 -0.0258 0.9566 0.1637
-3.500 -0.2634 0.00900 0.00325 -0.0267 0.9530 0.2367
-3.250 -0.2403 0.00827 0.00298 -0.0261 0.9467 0.3530
-3.000 -0.2147 0.00742 0.00273 -0.0260 0.9426 0.5102
-2.750 -0.1958 0.00686 0.00259 -0.0241 0.9353 0.6232
-2.500 -0.1702 0.00649 0.00246 -0.0235 0.9297 0.6976
-2.250 -0.1449 0.00625 0.00237 -0.0227 0.9237 0.7523
-2.000 -0.1183 0.00609 0.00231 -0.0221 0.9169 0.7939
-1.750 -0.0892 0.00598 0.00225 -0.0221 0.9111 0.8250
-1.500 -0.0617 0.00593 0.00222 -0.0218 0.9033 0.8506
-1.250 -0.0322 0.00590 0.00218 -0.0219 0.8966 0.8714
-1.000 -0.0026 0.00590 0.00218 -0.0219 0.8884 0.8882
-0.750 0.0276 0.00593 0.00219 -0.0222 0.8802 0.9023
-0.500 0.0597 0.00601 0.00225 -0.0228 0.8721 0.9174
-0.250 0.0931 0.00618 0.00240 -0.0235 0.8626 0.9316
0.000 0.1243 0.00631 0.00249 -0.0239 0.8528 0.9415
0.250 0.1653 0.00644 0.00256 -0.0266 0.8431 0.9448
0.500 0.2032 0.00654 0.00262 -0.0286 0.8306 0.9485
0.750 0.2316 0.00663 0.00265 -0.0286 0.8167 0.9551
1.000 0.2712 0.00671 0.00271 -0.0311 0.8031 0.9567
1.250 0.3092 0.00680 0.00275 -0.0333 0.7892 0.9589
1.500 0.3446 0.00689 0.00280 -0.0349 0.7746 0.9621
1.750 0.3727 0.00700 0.00286 -0.0349 0.7589 0.9678
2.000 0.4078 0.00707 0.00291 -0.0365 0.7371 0.9704
2.250 0.4436 0.00717 0.00294 -0.0382 0.7138 0.9728
2.500 0.4776 0.00727 0.00300 -0.0397 0.6917 0.9761
2.750 0.5077 0.00740 0.00309 -0.0402 0.6677 0.9805
3.000 0.5401 0.00752 0.00314 -0.0413 0.6384 0.9836
3.250 0.5736 0.00771 0.00317 -0.0427 0.5933 0.9863
3.500 0.6051 0.00795 0.00324 -0.0437 0.5424 0.9898
3.750 0.6338 0.00833 0.00337 -0.0442 0.4719 0.9936
4.000 0.6636 0.00894 0.00352 -0.0452 0.3648 0.9967
4.250 0.6927 0.00973 0.00379 -0.0463 0.2515 0.9998
4.500 0.7083 0.01038 0.00409 -0.0444 0.1739 1.0000
4.750 0.7218 0.01108 0.00446 -0.0420 0.1049 1.0000
5.000 0.7347 0.01184 0.00491 -0.0394 0.0480 1.0000
5.250 0.7489 0.01251 0.00550 -0.0368 0.0301 1.0000
5.500 0.7663 0.01289 0.00593 -0.0348 0.0260 1.0000
5.750 0.7814 0.01344 0.00652 -0.0324 0.0225 1.0000
6.000 0.7920 0.01434 0.00752 -0.0291 0.0203 1.0000
6.250 0.8081 0.01479 0.00804 -0.0269 0.0189 1.0000
6.500 0.8245 0.01519 0.00849 -0.0248 0.0170 1.0000
6.750 0.8383 0.01583 0.00917 -0.0222 0.0159 1.0000
7.000 0.8494 0.01672 0.01011 -0.0191 0.0149 1.0000
7.250 0.8564 0.01839 0.01190 -0.0153 0.0141 1.0000
7.500 0.8703 0.01963 0.01325 -0.0128 0.0136 1.0000
7.750 0.8866 0.02054 0.01428 -0.0106 0.0131 1.0000
8.000 0.9026 0.02178 0.01565 -0.0085 0.0127 1.0000
8.250 0.9186 0.02289 0.01690 -0.0064 0.0121 1.0000
8.500 0.9340 0.02382 0.01796 -0.0043 0.0114 1.0000
8.750 0.9484 0.02511 0.01938 -0.0022 0.0109 1.0000
9.000 0.9614 0.02661 0.02105 0.0001 0.0106 1.0000
9.250 0.9727 0.02829 0.02291 0.0026 0.0104 1.0000
9.500 0.9808 0.03041 0.02527 0.0056 0.0103 1.0000
9.750 0.9860 0.03264 0.02774 0.0088 0.0102 1.0000
10.000 0.9863 0.03522 0.03060 0.0125 0.0101 1.0000
10.250 0.9349 0.04443 0.04071 0.0228 0.0123 1.0000
10.500 0.9120 0.04771 0.04420 0.0283 0.0126 1.0000
10.750 0.8886 0.05130 0.04797 0.0322 0.0131 1.0000
11.000 0.8361 0.06096 0.05818 0.0356 0.0177 1.0000
11.250 0.8151 0.06525 0.06260 0.0352 0.0173 1.0000
11.500 0.7902 0.07108 0.06857 0.0328 0.0176 1.0000
11.750 0.7640 0.07856 0.07618 0.0279 0.0178 1.0000
12.000 0.7387 0.08790 0.08558 0.0211 0.0187 1.0000
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Polar data table (+)
Polar graphs
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