GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 500,000 Max Cl/Cd: 78.47 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe704-il-500000.txt Download as CSV file: xf-goe704-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6382 0.19651 0.19414 0.0341 1.0000 0.0228
-16.500 -0.6303 0.19328 0.19090 0.0323 1.0000 0.0237
-16.250 -0.9102 0.11021 0.10740 -0.0057 1.0000 0.0156
-16.000 -0.9518 0.09847 0.09549 -0.0123 1.0000 0.0154
-15.750 -0.9891 0.08784 0.08471 -0.0184 1.0000 0.0152
-15.500 -1.0232 0.07785 0.07454 -0.0244 1.0000 0.0151
-15.250 -1.0538 0.06806 0.06458 -0.0308 1.0000 0.0150
-15.000 -1.0770 0.05847 0.05478 -0.0383 1.0000 0.0150
-14.750 -1.0938 0.05004 0.04611 -0.0460 1.0000 0.0150
-14.500 -1.1062 0.04492 0.04082 -0.0490 1.0000 0.0151
-14.250 -1.1150 0.04137 0.03711 -0.0494 1.0000 0.0152
-14.000 -1.1204 0.03864 0.03425 -0.0485 1.0000 0.0154
-13.750 -1.1231 0.03640 0.03189 -0.0470 1.0000 0.0156
-13.500 -1.1236 0.03449 0.02984 -0.0449 1.0000 0.0158
-13.250 -1.1224 0.03281 0.02802 -0.0425 1.0000 0.0161
-13.000 -1.1195 0.03131 0.02639 -0.0399 1.0000 0.0164
-12.750 -1.1149 0.03000 0.02494 -0.0371 1.0000 0.0167
-12.500 -1.1069 0.02887 0.02368 -0.0346 1.0000 0.0171
-12.250 -1.0935 0.02790 0.02256 -0.0329 1.0000 0.0174
-12.000 -1.0897 0.02601 0.02057 -0.0299 1.0000 0.0180
-11.750 -1.0762 0.02490 0.01940 -0.0282 1.0000 0.0186
-11.500 -1.0596 0.02398 0.01842 -0.0267 1.0000 0.0192
-11.250 -1.0421 0.02310 0.01744 -0.0254 1.0000 0.0199
-11.000 -1.0235 0.02225 0.01649 -0.0241 1.0000 0.0206
-10.750 -1.0033 0.02153 0.01565 -0.0230 1.0000 0.0213
-10.500 -0.9887 0.02026 0.01432 -0.0211 1.0000 0.0223
-10.250 -0.9688 0.01951 0.01353 -0.0200 1.0000 0.0234
-10.000 -0.9476 0.01889 0.01284 -0.0190 1.0000 0.0247
-9.750 -0.9258 0.01837 0.01224 -0.0180 1.0000 0.0260
-9.500 -0.9094 0.01747 0.01134 -0.0163 1.0000 0.0280
-9.250 -0.8867 0.01696 0.01079 -0.0156 0.9981 0.0302
-9.000 -0.8528 0.01611 0.00990 -0.0173 0.9907 0.0337
-8.750 -0.8175 0.01558 0.00930 -0.0191 0.9818 0.0377
-8.500 -0.7859 0.01486 0.00860 -0.0202 0.9692 0.0438
-8.250 -0.7587 0.01431 0.00804 -0.0202 0.9524 0.0501
-8.000 -0.7352 0.01392 0.00759 -0.0192 0.9337 0.0561
-7.750 -0.7125 0.01359 0.00722 -0.0180 0.9164 0.0626
-7.500 -0.6895 0.01325 0.00687 -0.0170 0.9008 0.0702
-7.250 -0.6652 0.01300 0.00659 -0.0162 0.8870 0.0783
-7.000 -0.6397 0.01287 0.00638 -0.0155 0.8749 0.0859
-6.750 -0.6137 0.01268 0.00619 -0.0151 0.8636 0.0941
-6.500 -0.5871 0.01255 0.00599 -0.0148 0.8536 0.1008
-6.250 -0.5604 0.01248 0.00588 -0.0145 0.8446 0.1075
-6.000 -0.5329 0.01239 0.00571 -0.0144 0.8360 0.1133
-5.750 -0.5062 0.01228 0.00559 -0.0141 0.8285 0.1196
-5.500 -0.4782 0.01224 0.00547 -0.0141 0.8210 0.1243
-5.250 -0.4516 0.01200 0.00519 -0.0138 0.8141 0.1289
-5.000 -0.4244 0.01186 0.00502 -0.0136 0.8080 0.1336
-4.750 -0.3965 0.01175 0.00487 -0.0136 0.8015 0.1378
-4.500 -0.3691 0.01165 0.00467 -0.0134 0.7959 0.1414
-4.250 -0.3422 0.01138 0.00443 -0.0132 0.7902 0.1466
-4.000 -0.3146 0.01125 0.00428 -0.0131 0.7844 0.1512
-3.750 -0.2868 0.01118 0.00412 -0.0130 0.7794 0.1550
-3.500 -0.2598 0.01093 0.00390 -0.0129 0.7739 0.1606
-3.250 -0.2322 0.01077 0.00375 -0.0128 0.7683 0.1663
-3.000 -0.2044 0.01071 0.00361 -0.0126 0.7631 0.1713
-2.750 -0.1775 0.01046 0.00342 -0.0124 0.7559 0.1787
-2.500 -0.1503 0.01033 0.00325 -0.0122 0.7481 0.1857
-2.250 -0.1231 0.01014 0.00310 -0.0120 0.7407 0.1963
-2.000 -0.0958 0.00996 0.00298 -0.0119 0.7348 0.2112
-1.750 -0.0688 0.00980 0.00288 -0.0116 0.7297 0.2354
-1.500 -0.0420 0.00955 0.00281 -0.0115 0.7238 0.2746
-1.250 -0.0153 0.00932 0.00273 -0.0113 0.7182 0.3187
-1.000 0.0109 0.00910 0.00266 -0.0110 0.7129 0.3674
-0.750 0.0361 0.00874 0.00258 -0.0105 0.7067 0.4380
-0.500 0.0558 0.00801 0.00243 -0.0090 0.7009 0.5925
-0.250 0.0712 0.00728 0.00275 -0.0054 0.6954 0.8872
0.000 0.0989 0.00741 0.00289 -0.0048 0.6880 0.9130
0.250 0.1264 0.00757 0.00299 -0.0043 0.6802 0.9283
0.500 0.1528 0.00768 0.00309 -0.0035 0.6708 0.9403
0.750 0.1888 0.00791 0.00326 -0.0048 0.6624 0.9474
1.000 0.2183 0.00805 0.00337 -0.0048 0.6537 0.9557
1.250 0.2665 0.00830 0.00359 -0.0089 0.6443 0.9595
1.500 0.3102 0.00850 0.00372 -0.0121 0.6345 0.9636
1.750 0.3407 0.00860 0.00382 -0.0125 0.6237 0.9696
2.000 0.3973 0.00883 0.00400 -0.0184 0.6098 0.9734
2.250 0.4416 0.00901 0.00412 -0.0218 0.5918 0.9791
2.500 0.4848 0.00917 0.00419 -0.0251 0.5681 0.9843
2.750 0.5350 0.00932 0.00421 -0.0299 0.5377 0.9891
3.000 0.5749 0.00952 0.00428 -0.0326 0.5053 0.9938
3.250 0.6151 0.00966 0.00426 -0.0355 0.4685 0.9957
3.500 0.6537 0.00988 0.00430 -0.0381 0.4323 0.9981
3.750 0.6897 0.01013 0.00439 -0.0401 0.3992 1.0000
4.000 0.7151 0.01034 0.00449 -0.0399 0.3748 1.0000
4.250 0.7403 0.01056 0.00461 -0.0396 0.3545 1.0000
4.500 0.7653 0.01076 0.00474 -0.0393 0.3366 1.0000
4.750 0.7901 0.01096 0.00488 -0.0390 0.3202 1.0000
5.000 0.8146 0.01117 0.00503 -0.0386 0.3056 1.0000
5.250 0.8391 0.01137 0.00518 -0.0381 0.2925 1.0000
5.500 0.8634 0.01155 0.00534 -0.0376 0.2802 1.0000
5.750 0.8873 0.01175 0.00552 -0.0371 0.2688 1.0000
6.000 0.9109 0.01199 0.00571 -0.0365 0.2586 1.0000
6.250 0.9345 0.01218 0.00590 -0.0359 0.2492 1.0000
6.500 0.9577 0.01240 0.00610 -0.0352 0.2395 1.0000
6.750 0.9801 0.01267 0.00633 -0.0344 0.2291 1.0000
7.000 1.0029 0.01286 0.00653 -0.0337 0.2202 1.0000
7.250 1.0249 0.01312 0.00677 -0.0328 0.2119 1.0000
7.500 1.0466 0.01336 0.00701 -0.0319 0.2035 1.0000
7.750 1.0680 0.01361 0.00727 -0.0308 0.1965 1.0000
8.000 1.0885 0.01388 0.00753 -0.0297 0.1879 1.0000
8.250 1.1090 0.01414 0.00780 -0.0285 0.1802 1.0000
8.750 1.1470 0.01475 0.00840 -0.0257 0.1610 1.0000
9.000 1.1648 0.01509 0.00873 -0.0241 0.1508 1.0000
9.250 1.1811 0.01548 0.00908 -0.0223 0.1362 1.0000
9.500 1.1945 0.01601 0.00951 -0.0200 0.1160 1.0000
9.750 1.2042 0.01669 0.01005 -0.0171 0.0961 1.0000
10.000 1.2123 0.01736 0.01065 -0.0139 0.0848 1.0000
10.250 1.2201 0.01795 0.01124 -0.0106 0.0755 1.0000
10.500 1.2234 0.01868 0.01190 -0.0066 0.0595 1.0000
11.000 1.2047 0.02076 0.01372 0.0053 0.0280 1.0000
11.250 1.2087 0.02168 0.01468 0.0085 0.0253 1.0000
11.500 1.2122 0.02290 0.01595 0.0112 0.0230 1.0000
11.750 1.2216 0.02390 0.01703 0.0130 0.0218 1.0000
12.000 1.2296 0.02512 0.01832 0.0146 0.0208 1.0000
12.250 1.2356 0.02658 0.01985 0.0162 0.0199 1.0000
12.500 1.2375 0.02847 0.02182 0.0177 0.0191 1.0000
12.750 1.2401 0.03042 0.02387 0.0189 0.0185 1.0000
13.000 1.2460 0.03217 0.02572 0.0197 0.0180 1.0000
13.250 1.2501 0.03415 0.02781 0.0205 0.0176 1.0000
13.500 1.2528 0.03634 0.03009 0.0211 0.0171 1.0000
13.750 1.2541 0.03872 0.03255 0.0215 0.0166 1.0000
14.000 1.2534 0.04137 0.03529 0.0218 0.0163 1.0000
14.250 1.2502 0.04438 0.03839 0.0219 0.0159 1.0000
14.500 1.2435 0.04786 0.04196 0.0219 0.0156 1.0000
14.750 1.2333 0.05188 0.04608 0.0215 0.0153 1.0000
15.000 1.2216 0.05625 0.05055 0.0210 0.0151 1.0000
15.250 1.2206 0.05957 0.05398 0.0203 0.0149 1.0000
15.500 1.2177 0.06324 0.05776 0.0193 0.0147 1.0000
15.750 1.2137 0.06713 0.06175 0.0183 0.0145 1.0000
16.000 1.2090 0.07119 0.06592 0.0171 0.0144 1.0000
16.250 1.2041 0.07537 0.07020 0.0158 0.0142 1.0000
16.500 1.1991 0.07960 0.07452 0.0145 0.0140 1.0000
16.750 1.1940 0.08387 0.07889 0.0131 0.0138 1.0000
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