GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 200,000 Max Cl/Cd: 57.47 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe704-il-200000-n5.txt Download as CSV file: xf-goe704-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7946 0.11187 0.10799 -0.0061 1.0000 0.0176
-14.750 -0.8369 0.09966 0.09560 -0.0126 1.0000 0.0173
-14.500 -0.8724 0.08908 0.08487 -0.0184 1.0000 0.0170
-14.250 -0.9063 0.07876 0.07438 -0.0245 1.0000 0.0168
-14.000 -0.9362 0.06903 0.06452 -0.0308 1.0000 0.0167
-13.750 -0.9647 0.05767 0.05297 -0.0403 1.0000 0.0165
-13.500 -0.9866 0.04934 0.04436 -0.0474 1.0000 0.0164
-13.250 -1.0006 0.04492 0.03972 -0.0486 1.0000 0.0166
-13.000 -1.0096 0.04176 0.03633 -0.0478 1.0000 0.0168
-12.750 -1.0174 0.03914 0.03359 -0.0460 1.0000 0.0171
-12.500 -1.0214 0.03704 0.03136 -0.0436 1.0000 0.0175
-12.250 -1.0215 0.03533 0.02952 -0.0409 1.0000 0.0180
-12.000 -1.0185 0.03384 0.02790 -0.0383 1.0000 0.0185
-11.750 -1.0108 0.03239 0.02631 -0.0362 1.0000 0.0193
-11.500 -1.0010 0.03100 0.02476 -0.0342 1.0000 0.0201
-11.250 -0.9893 0.02969 0.02326 -0.0323 1.0000 0.0210
-11.000 -0.9774 0.02836 0.02182 -0.0305 1.0000 0.0218
-10.750 -0.9632 0.02719 0.02055 -0.0289 1.0000 0.0229
-10.500 -0.9468 0.02616 0.01939 -0.0275 1.0000 0.0244
-10.250 -0.9291 0.02520 0.01827 -0.0261 1.0000 0.0263
-10.000 -0.9123 0.02418 0.01721 -0.0247 1.0000 0.0283
-9.750 -0.8936 0.02333 0.01626 -0.0235 1.0000 0.0310
-9.500 -0.8755 0.02248 0.01532 -0.0221 1.0000 0.0339
-9.250 -0.8572 0.02175 0.01453 -0.0207 1.0000 0.0375
-9.000 -0.8319 0.02097 0.01368 -0.0208 0.9927 0.0421
-8.750 -0.7999 0.02026 0.01284 -0.0221 0.9801 0.0480
-8.500 -0.7690 0.01953 0.01210 -0.0232 0.9672 0.0541
-8.250 -0.7383 0.01894 0.01143 -0.0241 0.9543 0.0606
-8.000 -0.7086 0.01846 0.01087 -0.0248 0.9412 0.0678
-7.750 -0.6804 0.01806 0.01045 -0.0250 0.9278 0.0751
-7.500 -0.6535 0.01775 0.01007 -0.0248 0.9141 0.0831
-7.250 -0.6273 0.01755 0.00977 -0.0244 0.9008 0.0915
-7.000 -0.6019 0.01731 0.00949 -0.0239 0.8889 0.0981
-6.750 -0.5761 0.01709 0.00912 -0.0234 0.8779 0.1043
-6.500 -0.5510 0.01681 0.00877 -0.0228 0.8674 0.1095
-6.250 -0.5254 0.01661 0.00849 -0.0223 0.8576 0.1152
-6.000 -0.4994 0.01643 0.00814 -0.0218 0.8493 0.1204
-5.750 -0.4738 0.01612 0.00782 -0.0213 0.8404 0.1253
-5.500 -0.4479 0.01593 0.00754 -0.0209 0.8331 0.1304
-5.250 -0.4211 0.01575 0.00723 -0.0206 0.8254 0.1353
-5.000 -0.3954 0.01546 0.00692 -0.0202 0.8189 0.1399
-4.750 -0.3688 0.01523 0.00665 -0.0199 0.8119 0.1449
-4.500 -0.3420 0.01506 0.00637 -0.0196 0.8055 0.1500
-4.250 -0.3157 0.01480 0.00610 -0.0193 0.7998 0.1552
-4.000 -0.2890 0.01458 0.00586 -0.0191 0.7934 0.1606
-3.750 -0.2623 0.01441 0.00561 -0.0188 0.7880 0.1659
-3.500 -0.2357 0.01417 0.00538 -0.0185 0.7824 0.1714
-3.250 -0.2090 0.01397 0.00517 -0.0183 0.7764 0.1773
-3.000 -0.1822 0.01381 0.00496 -0.0180 0.7714 0.1834
-2.500 -0.1287 0.01343 0.00464 -0.0176 0.7599 0.2013
-2.250 -0.1022 0.01327 0.00449 -0.0172 0.7547 0.2148
-2.000 -0.0756 0.01308 0.00438 -0.0170 0.7481 0.2321
-1.750 -0.0495 0.01289 0.00425 -0.0166 0.7404 0.2551
-1.500 -0.0234 0.01270 0.00413 -0.0162 0.7312 0.2830
-1.250 0.0023 0.01250 0.00399 -0.0157 0.7230 0.3151
-1.000 0.0280 0.01226 0.00392 -0.0153 0.7150 0.3549
-0.750 0.0527 0.01197 0.00382 -0.0147 0.7086 0.4087
-0.500 0.0752 0.01152 0.00372 -0.0137 0.7019 0.4952
-0.250 0.1184 0.01080 0.00437 -0.0155 0.6947 0.8608
0.000 0.1470 0.01098 0.00449 -0.0151 0.6878 0.8946
0.250 0.1750 0.01113 0.00462 -0.0148 0.6795 0.9151
0.500 0.2052 0.01132 0.00474 -0.0148 0.6717 0.9304
0.750 0.2411 0.01150 0.00488 -0.0162 0.6618 0.9415
1.000 0.2833 0.01168 0.00501 -0.0189 0.6499 0.9502
1.250 0.3237 0.01186 0.00512 -0.0212 0.6358 0.9611
1.500 0.3684 0.01204 0.00525 -0.0245 0.6198 0.9720
1.750 0.4205 0.01216 0.00530 -0.0295 0.6028 0.9807
2.000 0.4645 0.01221 0.00530 -0.0329 0.5852 0.9873
2.250 0.5033 0.01225 0.00526 -0.0353 0.5662 0.9921
2.500 0.5430 0.01228 0.00521 -0.0379 0.5421 0.9962
2.750 0.5821 0.01236 0.00517 -0.0404 0.5132 0.9999
3.000 0.6071 0.01252 0.00518 -0.0400 0.4839 1.0000
3.250 0.6315 0.01273 0.00523 -0.0395 0.4524 1.0000
3.500 0.6556 0.01299 0.00532 -0.0391 0.4228 1.0000
3.750 0.6795 0.01326 0.00546 -0.0385 0.3968 1.0000
4.000 0.7034 0.01352 0.00562 -0.0380 0.3752 1.0000
4.250 0.7271 0.01376 0.00580 -0.0375 0.3575 1.0000
4.500 0.7506 0.01401 0.00599 -0.0369 0.3419 1.0000
4.750 0.7738 0.01427 0.00620 -0.0362 0.3275 1.0000
5.000 0.7967 0.01455 0.00643 -0.0355 0.3137 1.0000
5.250 0.8191 0.01484 0.00667 -0.0347 0.3005 1.0000
5.500 0.8415 0.01510 0.00692 -0.0339 0.2881 1.0000
5.750 0.8637 0.01536 0.00719 -0.0330 0.2778 1.0000
6.000 0.8850 0.01567 0.00747 -0.0321 0.2687 1.0000
6.250 0.9065 0.01594 0.00777 -0.0310 0.2590 1.0000
6.500 0.9272 0.01624 0.00808 -0.0299 0.2507 1.0000
6.750 0.9477 0.01655 0.00840 -0.0288 0.2432 1.0000
7.000 0.9677 0.01686 0.00874 -0.0275 0.2367 1.0000
7.250 0.9874 0.01718 0.00910 -0.0262 0.2293 1.0000
7.500 1.0061 0.01754 0.00947 -0.0247 0.2228 1.0000
7.750 1.0250 0.01786 0.00985 -0.0233 0.2164 1.0000
8.000 1.0420 0.01826 0.01025 -0.0216 0.2094 1.0000
8.250 1.0598 0.01859 0.01065 -0.0199 0.2012 1.0000
8.500 1.0755 0.01901 0.01108 -0.0180 0.1925 1.0000
8.750 1.0906 0.01942 0.01150 -0.0160 0.1828 1.0000
9.000 1.1054 0.01982 0.01195 -0.0139 0.1736 1.0000
9.250 1.1179 0.02031 0.01243 -0.0115 0.1642 1.0000
9.500 1.1305 0.02076 0.01291 -0.0091 0.1531 1.0000
9.750 1.1423 0.02124 0.01341 -0.0066 0.1418 1.0000
10.000 1.1522 0.02179 0.01397 -0.0039 0.1282 1.0000
10.250 1.1588 0.02245 0.01458 -0.0007 0.1128 1.0000
10.500 1.1597 0.02325 0.01529 0.0033 0.0989 1.0000
10.750 1.1610 0.02424 0.01620 0.0068 0.0886 1.0000
11.000 1.1664 0.02524 0.01722 0.0094 0.0806 1.0000
11.250 1.1721 0.02639 0.01839 0.0117 0.0722 1.0000
11.500 1.1798 0.02753 0.01957 0.0136 0.0588 1.0000
11.750 1.1781 0.02948 0.02135 0.0158 0.0359 1.0000
12.000 1.1775 0.03149 0.02332 0.0176 0.0285 1.0000
12.250 1.1786 0.03348 0.02536 0.0190 0.0251 1.0000
12.500 1.1812 0.03545 0.02742 0.0201 0.0230 1.0000
12.750 1.1838 0.03751 0.02960 0.0210 0.0215 1.0000
13.000 1.1845 0.03982 0.03202 0.0218 0.0205 1.0000
13.250 1.1828 0.04246 0.03478 0.0223 0.0196 1.0000
13.500 1.1795 0.04538 0.03781 0.0226 0.0190 1.0000
13.750 1.1783 0.04818 0.04077 0.0227 0.0184 1.0000
14.000 1.1755 0.05129 0.04401 0.0226 0.0179 1.0000
14.250 1.1709 0.05470 0.04756 0.0222 0.0174 1.0000
14.500 1.1651 0.05843 0.05145 0.0216 0.0169 1.0000
14.750 1.1579 0.06254 0.05570 0.0206 0.0165 1.0000
15.000 1.1497 0.06700 0.06030 0.0192 0.0162 1.0000
15.250 1.1402 0.07184 0.06526 0.0176 0.0159 1.0000
15.500 1.1297 0.07701 0.07057 0.0157 0.0156 1.0000
15.750 1.1181 0.08247 0.07615 0.0136 0.0154 1.0000
16.000 1.1061 0.08812 0.08192 0.0114 0.0152 1.0000
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