GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 744 AIRFOIL (goe744-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.92 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe744-il-1000000-n5.txt Download as CSV file: xf-goe744-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 744 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2122 0.08720 0.08375 0.0008 0.4636 0.0186
-7.750 -0.2101 0.08418 0.08074 -0.0007 0.4619 0.0187
-7.250 -0.2150 0.07830 0.07489 -0.0032 0.4585 0.0188
-6.250 -0.3253 0.02148 0.01636 -0.0204 0.4593 0.0217
-6.000 -0.3059 0.01910 0.01361 -0.0193 0.4579 0.0220
-5.750 -0.2822 0.01778 0.01207 -0.0186 0.4563 0.0222
-5.500 -0.2572 0.01678 0.01089 -0.0179 0.4543 0.0224
-5.250 -0.2313 0.01596 0.00992 -0.0173 0.4524 0.0226
-5.000 -0.2046 0.01530 0.00911 -0.0169 0.4502 0.0227
-4.750 -0.1776 0.01471 0.00840 -0.0164 0.4478 0.0229
-4.500 -0.1502 0.01422 0.00779 -0.0160 0.4452 0.0231
-4.250 -0.1225 0.01378 0.00725 -0.0157 0.4425 0.0232
-4.000 -0.0946 0.01340 0.00679 -0.0154 0.4405 0.0233
-3.750 -0.0664 0.01306 0.00638 -0.0151 0.4389 0.0234
-3.500 -0.0384 0.01267 0.00592 -0.0148 0.4368 0.0236
-3.250 -0.0104 0.01227 0.00547 -0.0145 0.4343 0.0238
-3.000 0.0180 0.01200 0.00517 -0.0143 0.4318 0.0241
-2.750 0.0466 0.01180 0.00493 -0.0141 0.4294 0.0243
-2.500 0.0753 0.01164 0.00475 -0.0139 0.4266 0.0246
-2.250 0.1041 0.01149 0.00457 -0.0138 0.4237 0.0249
-2.000 0.1328 0.01132 0.00438 -0.0136 0.4217 0.0252
-1.750 0.1615 0.01113 0.00418 -0.0135 0.4195 0.0255
-1.500 0.1902 0.01096 0.00398 -0.0133 0.4168 0.0258
-1.250 0.2189 0.01080 0.00379 -0.0132 0.4137 0.0261
-1.000 0.2476 0.01067 0.00362 -0.0131 0.4105 0.0264
-0.750 0.2763 0.01056 0.00348 -0.0130 0.4073 0.0267
-0.500 0.3050 0.01044 0.00335 -0.0129 0.4051 0.0269
-0.250 0.3335 0.01027 0.00319 -0.0127 0.4021 0.0273
0.000 0.3621 0.01017 0.00308 -0.0126 0.3986 0.0278
0.250 0.3907 0.01011 0.00301 -0.0125 0.3951 0.0283
0.500 0.4192 0.01007 0.00295 -0.0125 0.3913 0.0288
0.750 0.4478 0.01001 0.00289 -0.0124 0.3882 0.0294
1.000 0.4764 0.00996 0.00284 -0.0123 0.3846 0.0300
1.250 0.5050 0.00994 0.00281 -0.0123 0.3806 0.0307
1.500 0.5332 0.00991 0.00278 -0.0122 0.3767 0.0317
1.750 0.5616 0.00990 0.00277 -0.0122 0.3735 0.0327
2.000 0.5900 0.00989 0.00277 -0.0121 0.3701 0.0338
2.250 0.6183 0.00989 0.00277 -0.0121 0.3659 0.0349
2.500 0.6464 0.00992 0.00279 -0.0121 0.3618 0.0364
2.750 0.6745 0.00996 0.00283 -0.0120 0.3583 0.0384
3.000 0.7027 0.00997 0.00286 -0.0120 0.3554 0.0407
3.250 0.7309 0.01000 0.00290 -0.0120 0.3519 0.0439
3.500 0.7588 0.01005 0.00296 -0.0120 0.3478 0.0479
3.750 0.7864 0.01014 0.00304 -0.0120 0.3433 0.0525
4.000 0.8142 0.01017 0.00310 -0.0119 0.3400 0.0609
4.250 0.8406 0.01011 0.00320 -0.0117 0.3360 0.1296
4.500 0.8674 0.01015 0.00335 -0.0116 0.3320 0.1869
4.750 0.8947 0.01026 0.00349 -0.0116 0.3279 0.2061
5.000 0.9220 0.01033 0.00360 -0.0116 0.3250 0.2277
5.250 0.9491 0.01038 0.00373 -0.0115 0.3216 0.2595
5.500 0.9570 0.00941 0.00388 -0.0079 0.3185 0.7765
6.500 1.1382 0.01010 0.00496 -0.0232 0.2998 0.9847
6.750 1.1724 0.01037 0.00519 -0.0249 0.2957 0.9864
7.000 1.2039 0.01054 0.00537 -0.0259 0.2928 0.9877
7.250 1.2343 0.01075 0.00557 -0.0268 0.2893 0.9890
7.500 1.2644 0.01102 0.00581 -0.0276 0.2854 0.9906
7.750 1.2939 0.01134 0.00612 -0.0285 0.2813 0.9924
8.000 1.3249 0.01157 0.00635 -0.0296 0.2785 0.9934
8.250 1.3560 0.01180 0.00657 -0.0307 0.2754 0.9940
8.500 1.3860 0.01208 0.00685 -0.0317 0.2715 0.9947
8.750 1.4174 0.01244 0.00720 -0.0332 0.2672 0.9957
9.000 1.4475 0.01277 0.00752 -0.0344 0.2638 0.9967
9.250 1.4766 0.01305 0.00782 -0.0353 0.2610 0.9974
9.500 1.5074 0.01338 0.00816 -0.0367 0.2579 0.9985
9.750 1.5389 0.01378 0.00857 -0.0383 0.2546 0.9995
10.000 1.5657 0.01428 0.00906 -0.0392 0.2512 1.0000
10.250 1.5849 0.01474 0.00954 -0.0386 0.2488 1.0000
10.500 1.6035 0.01519 0.01003 -0.0379 0.2468 1.0000
10.750 1.6197 0.01577 0.01064 -0.0370 0.2443 1.0000
11.000 1.6310 0.01683 0.01174 -0.0364 0.2414 1.0000
11.250 1.6224 0.01840 0.01336 -0.0333 0.2394 1.0000
11.500 1.6131 0.02015 0.01514 -0.0303 0.2364 1.0000
11.750 1.6126 0.02170 0.01672 -0.0284 0.2340 1.0000
12.000 1.6166 0.02309 0.01815 -0.0271 0.2313 1.0000
12.250 1.6178 0.02477 0.01986 -0.0258 0.2279 1.0000
12.500 1.6150 0.02685 0.02196 -0.0245 0.2243 1.0000
12.750 1.6076 0.02939 0.02451 -0.0233 0.2200 1.0000
13.000 1.6113 0.03108 0.02625 -0.0225 0.2178 1.0000
13.250 1.6141 0.03288 0.02809 -0.0217 0.2158 1.0000
13.500 1.6154 0.03483 0.03008 -0.0210 0.2132 1.0000
13.750 1.6142 0.03706 0.03235 -0.0203 0.2110 1.0000
14.000 1.6112 0.03957 0.03488 -0.0198 0.2082 1.0000
14.250 1.6092 0.04203 0.03737 -0.0194 0.2049 1.0000
14.500 1.6130 0.04401 0.03940 -0.0191 0.2028 1.0000
14.750 1.6167 0.04600 0.04144 -0.0188 0.2005 1.0000
15.000 1.6171 0.04835 0.04382 -0.0186 0.1976 1.0000
15.250 1.6123 0.05129 0.04677 -0.0185 0.1939 1.0000
15.500 1.6113 0.05387 0.04938 -0.0184 0.1909 1.0000
15.750 1.6149 0.05600 0.05156 -0.0183 0.1886 1.0000
16.000 1.6179 0.05818 0.05378 -0.0183 0.1856 1.0000
16.250 1.6143 0.06115 0.05678 -0.0184 0.1821 1.0000
16.500 1.6089 0.06433 0.05997 -0.0185 0.1776 1.0000
16.750 1.6118 0.06662 0.06230 -0.0186 0.1749 1.0000
17.000 1.6115 0.06932 0.06504 -0.0188 0.1719 1.0000
17.250 1.6080 0.07237 0.06811 -0.0191 0.1679 1.0000
17.500 1.6027 0.07569 0.07147 -0.0194 0.1646 1.0000
17.750 1.6026 0.07843 0.07423 -0.0197 0.1601 1.0000
18.000 1.5915 0.08254 0.07837 -0.0203 0.1548 1.0000
18.250 1.5859 0.08599 0.08183 -0.0208 0.1493 1.0000
18.500 1.5693 0.09091 0.08675 -0.0216 0.1422 1.0000
18.750 1.5657 0.09421 0.09008 -0.0223 0.1377 1.0000
19.000 1.5439 0.09991 0.09577 -0.0234 0.1291 1.0000
19.250 1.5377 0.10365 0.09955 -0.0242 0.1241 1.0000
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