GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.66 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe54-il-1000000.txt Download as CSV file: xf-goe54-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5822 0.10986 0.10833 0.0452 1.0000 0.0142
-8.500 -0.5787 0.10600 0.10448 0.0423 1.0000 0.0143
-8.250 -0.5767 0.10196 0.10046 0.0386 1.0000 0.0143
-8.000 -0.5720 0.09784 0.09635 0.0380 1.0000 0.0144
-7.750 -0.5654 0.09457 0.09310 0.0371 1.0000 0.0145
-7.500 -0.5556 0.09121 0.08975 0.0345 1.0000 0.0146
-7.250 -0.5435 0.08772 0.08627 0.0312 1.0000 0.0148
-7.000 -0.5294 0.08406 0.08262 0.0272 1.0000 0.0151
-6.750 -0.5132 0.08022 0.07877 0.0228 1.0000 0.0154
-6.500 -0.4950 0.07617 0.07470 0.0181 1.0000 0.0160
-6.250 -0.4682 0.07098 0.06946 0.0105 1.0000 0.0170
-6.000 -0.4325 0.06423 0.06255 0.0000 1.0000 0.0171
-5.750 -0.4156 0.06029 0.05774 -0.0021 0.6921 0.0172
-5.500 -0.3994 0.05744 0.05459 -0.0029 0.5958 0.0173
-5.250 -0.3785 0.05470 0.05158 -0.0047 0.5269 0.0175
-5.000 -0.3548 0.05189 0.04860 -0.0067 0.4973 0.0177
-4.750 -0.3292 0.04904 0.04561 -0.0088 0.4788 0.0181
-4.500 -0.3020 0.04613 0.04255 -0.0108 0.4653 0.0187
-4.250 -0.2600 0.04237 0.03844 -0.0135 0.4553 0.0202
-4.000 -0.2304 0.03932 0.03517 -0.0146 0.4465 0.0202
-3.750 -0.2050 0.03538 0.03106 -0.0160 0.4382 0.0204
-3.500 -0.1805 0.03317 0.02877 -0.0168 0.4306 0.0206
-3.250 -0.1544 0.03130 0.02680 -0.0175 0.4227 0.0208
-3.000 -0.1273 0.02962 0.02501 -0.0180 0.4158 0.0212
-2.750 -0.0990 0.02795 0.02319 -0.0184 0.4086 0.0218
-2.500 -0.0650 0.02674 0.02169 -0.0178 0.4021 0.0236
-2.250 -0.0344 0.02531 0.02001 -0.0177 0.3951 0.0237
-2.000 -0.0052 0.02385 0.01834 -0.0177 0.3872 0.0237
-1.750 0.0225 0.02095 0.01531 -0.0185 0.3795 0.0241
-1.500 0.0502 0.01975 0.01402 -0.0189 0.3705 0.0243
-1.250 0.0785 0.01872 0.01289 -0.0190 0.3605 0.0247
-1.000 0.1073 0.01781 0.01183 -0.0191 0.3480 0.0253
-0.750 0.1366 0.01701 0.01086 -0.0190 0.3310 0.0266
-0.500 0.1674 0.01731 0.01081 -0.0181 0.3100 0.0277
-0.250 0.1964 0.01667 0.00995 -0.0180 0.2893 0.0277
0.000 0.2250 0.01467 0.00784 -0.0185 0.2734 0.0283
0.250 0.2534 0.01406 0.00715 -0.0186 0.2612 0.0288
0.500 0.2820 0.01359 0.00661 -0.0186 0.2525 0.0296
0.750 0.3108 0.01320 0.00611 -0.0185 0.2448 0.0308
1.000 0.3399 0.01367 0.00640 -0.0179 0.2401 0.0323
1.250 0.3687 0.01235 0.00503 -0.0180 0.2354 0.0332
1.500 0.3971 0.01192 0.00460 -0.0180 0.2305 0.0341
1.750 0.4257 0.01165 0.00432 -0.0179 0.2281 0.0359
2.000 0.4543 0.01217 0.00471 -0.0175 0.2251 0.0378
2.250 0.4828 0.01110 0.00371 -0.0176 0.2221 0.0393
2.500 0.5111 0.01090 0.00353 -0.0176 0.2186 0.0414
3.500 0.6255 0.01018 0.00282 -0.0171 0.2083 0.0366
3.750 0.6541 0.01010 0.00274 -0.0170 0.2052 0.0365
4.000 0.6825 0.01013 0.00275 -0.0170 0.2013 0.0370
4.250 0.7108 0.01015 0.00279 -0.0169 0.1988 0.0380
4.500 0.7395 0.01005 0.00272 -0.0169 0.1962 0.0385
4.750 0.7679 0.01004 0.00272 -0.0168 0.1926 0.0402
5.000 0.7961 0.01010 0.00278 -0.0168 0.1884 0.0421
5.250 0.8243 0.01020 0.00288 -0.0167 0.1840 0.0442
5.500 0.8526 0.01020 0.00289 -0.0166 0.1785 0.0499
5.750 0.8796 0.00888 0.00318 -0.0170 0.1712 0.8687
6.000 0.9050 0.00875 0.00323 -0.0162 0.1660 1.0000
6.250 0.9329 0.00895 0.00337 -0.0161 0.1572 1.0000
6.500 0.9607 0.00913 0.00353 -0.0161 0.1499 1.0000
6.750 0.9884 0.00937 0.00373 -0.0160 0.1425 1.0000
7.000 1.0161 0.00958 0.00393 -0.0159 0.1378 1.0000
7.250 1.0436 0.00985 0.00418 -0.0159 0.1322 1.0000
7.500 1.0712 0.01007 0.00442 -0.0158 0.1284 1.0000
7.750 1.0986 0.01030 0.00466 -0.0157 0.1252 1.0000
8.000 1.1259 0.01057 0.00493 -0.0156 0.1212 1.0000
8.250 1.1531 0.01087 0.00524 -0.0156 0.1167 1.0000
8.500 1.1804 0.01107 0.00547 -0.0155 0.1130 1.0000
8.750 1.2072 0.01141 0.00579 -0.0154 0.1071 1.0000
9.000 1.2343 0.01166 0.00608 -0.0153 0.1024 1.0000
9.250 1.2609 0.01201 0.00641 -0.0152 0.0941 1.0000
9.500 1.2867 0.01256 0.00685 -0.0152 0.0736 1.0000
9.750 1.3108 0.01360 0.00774 -0.0151 0.0530 1.0000
10.000 1.3363 0.01418 0.00834 -0.0150 0.0477 1.0000
10.250 1.3612 0.01489 0.00906 -0.0149 0.0427 1.0000
10.500 1.3869 0.01532 0.00955 -0.0147 0.0406 1.0000
10.750 1.4117 0.01594 0.01021 -0.0146 0.0378 1.0000
11.000 1.4361 0.01663 0.01095 -0.0144 0.0351 1.0000
11.250 1.4611 0.01709 0.01147 -0.0142 0.0334 1.0000
11.500 1.4852 0.01774 0.01216 -0.0141 0.0311 1.0000
11.750 1.5084 0.01853 0.01299 -0.0138 0.0287 1.0000
12.000 1.5326 0.01905 0.01358 -0.0136 0.0271 1.0000
12.250 1.5553 0.01984 0.01440 -0.0134 0.0249 1.0000
12.500 1.5774 0.02069 0.01532 -0.0131 0.0231 1.0000
12.750 1.5999 0.02141 0.01610 -0.0129 0.0214 1.0000
13.000 1.6198 0.02253 0.01726 -0.0126 0.0195 1.0000
13.250 1.6408 0.02339 0.01821 -0.0123 0.0183 1.0000
13.500 1.6606 0.02437 0.01926 -0.0120 0.0171 1.0000
13.750 1.6772 0.02578 0.02073 -0.0116 0.0159 1.0000
14.000 1.6928 0.02722 0.02229 -0.0112 0.0151 1.0000
14.250 1.7085 0.02852 0.02370 -0.0109 0.0145 1.0000
14.500 1.7213 0.03012 0.02541 -0.0105 0.0139 1.0000
14.750 1.7290 0.03224 0.02764 -0.0104 0.0133 1.0000
15.000 1.7260 0.03542 0.03098 -0.0106 0.0129 1.0000
15.250 1.6946 0.04763 0.04355 -0.0232 0.0132 1.0000
15.500 1.6421 0.06019 0.05634 -0.0311 0.0136 1.0000
15.750 1.5852 0.07241 0.06876 -0.0373 0.0141 1.0000
16.000 1.5331 0.08404 0.08056 -0.0429 0.0146 1.0000
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Polar data table (+)
Polar graphs
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