GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 744 AIRFOIL (goe744-il) Reynolds number: 500,000 Max Cl/Cd: 98.9 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe744-il-500000.txt Download as CSV file: xf-goe744-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1977 0.09717 0.09325 0.0045 0.5182 0.0316
-8.000 -0.2165 0.09327 0.08939 -0.0012 0.5176 0.0321
-7.750 -0.2224 0.08986 0.08602 -0.0041 0.5163 0.0321
-7.500 -0.2108 0.08679 0.08297 -0.0037 0.5143 0.0323
-7.250 -0.1992 0.08434 0.08053 -0.0035 0.5121 0.0324
-7.000 -0.1937 0.08194 0.07813 -0.0038 0.5100 0.0326
-6.750 -0.1870 0.07974 0.07593 -0.0040 0.5079 0.0328
-6.500 -0.1786 0.07727 0.07345 -0.0051 0.5060 0.0330
-6.250 -0.1696 0.07474 0.07088 -0.0064 0.5040 0.0333
-6.000 -0.1595 0.07217 0.06827 -0.0079 0.5018 0.0337
-5.750 -0.1482 0.06945 0.06553 -0.0096 0.4998 0.0342
-5.500 -0.1354 0.06650 0.06256 -0.0116 0.4983 0.0350
-5.250 -0.1229 0.05940 0.05527 -0.0186 0.4973 0.0366
-5.000 -0.1069 0.05726 0.05313 -0.0185 0.4950 0.0368
-4.750 -0.0892 0.05524 0.05110 -0.0186 0.4926 0.0370
-4.500 -0.0706 0.05326 0.04908 -0.0189 0.4904 0.0374
-4.250 -0.0509 0.05110 0.04686 -0.0194 0.4883 0.0378
-4.000 -0.0249 0.04306 0.03833 -0.0231 0.4870 0.0413
-3.750 -0.0063 0.04154 0.03680 -0.0227 0.4846 0.0416
-3.500 0.0139 0.04034 0.03555 -0.0224 0.4817 0.0418
-3.250 0.0359 0.03890 0.03410 -0.0222 0.4798 0.0422
-3.000 0.0587 0.03739 0.03255 -0.0221 0.4777 0.0428
-2.750 0.0805 0.03098 0.02550 -0.0214 0.4761 0.0469
-2.500 0.1041 0.02985 0.02443 -0.0212 0.4736 0.0473
-2.250 0.1285 0.02901 0.02357 -0.0209 0.4710 0.0479
-2.000 0.1531 0.02803 0.02251 -0.0205 0.4685 0.0488
-1.750 0.1755 0.02473 0.01863 -0.0190 0.4665 0.0534
-1.500 0.2006 0.02389 0.01774 -0.0187 0.4636 0.0541
-1.250 0.2267 0.02298 0.01682 -0.0184 0.4616 0.0553
-1.000 0.2521 0.02145 0.01492 -0.0174 0.4592 0.0605
-0.750 0.2787 0.01701 0.00949 -0.0149 0.4570 0.0416
-0.500 0.3068 0.01624 0.00868 -0.0148 0.4543 0.0423
-0.250 0.3352 0.01577 0.00819 -0.0147 0.4517 0.0431
0.000 0.3638 0.01524 0.00755 -0.0144 0.4490 0.0434
0.250 0.3923 0.01487 0.00705 -0.0143 0.4458 0.0437
0.500 0.4213 0.01445 0.00663 -0.0142 0.4435 0.0443
0.750 0.4501 0.01409 0.00626 -0.0141 0.4406 0.0451
1.000 0.4788 0.01381 0.00594 -0.0140 0.4375 0.0459
1.250 0.5073 0.01356 0.00566 -0.0138 0.4345 0.0467
1.500 0.5347 0.01319 0.00531 -0.0136 0.4317 0.0485
1.750 0.5622 0.01311 0.00520 -0.0134 0.4284 0.0505
2.000 0.5903 0.01294 0.00508 -0.0133 0.4256 0.0522
2.250 0.6173 0.01268 0.00488 -0.0129 0.4224 0.0544
2.500 0.6448 0.01254 0.00476 -0.0127 0.4191 0.0572
2.750 0.6720 0.01242 0.00463 -0.0125 0.4160 0.0612
3.000 0.6990 0.01240 0.00458 -0.0122 0.4126 0.0681
3.250 0.7256 0.01227 0.00460 -0.0119 0.4098 0.0957
3.500 0.7510 0.01205 0.00475 -0.0114 0.4065 0.2255
3.750 0.7772 0.01194 0.00481 -0.0112 0.4031 0.2837
4.000 0.8692 0.01082 0.00523 -0.0243 0.3977 0.9793
4.250 0.9818 0.01095 0.00528 -0.0417 0.3919 1.0000
4.500 1.0084 0.01104 0.00535 -0.0415 0.3883 1.0000
4.750 1.0349 0.01116 0.00542 -0.0414 0.3847 1.0000
5.000 1.0610 0.01132 0.00551 -0.0412 0.3810 1.0000
5.250 1.0872 0.01148 0.00566 -0.0410 0.3775 1.0000
5.500 1.1135 0.01161 0.00580 -0.0408 0.3736 1.0000
5.750 1.1394 0.01175 0.00593 -0.0406 0.3695 1.0000
6.000 1.1649 0.01196 0.00607 -0.0404 0.3656 1.0000
6.250 1.1904 0.01218 0.00628 -0.0402 0.3619 1.0000
6.500 1.2160 0.01235 0.00648 -0.0400 0.3581 1.0000
6.750 1.2412 0.01255 0.00668 -0.0398 0.3542 1.0000
7.000 1.2659 0.01281 0.00688 -0.0396 0.3503 1.0000
7.250 1.2901 0.01309 0.00716 -0.0393 0.3465 1.0000
7.500 1.3148 0.01331 0.00742 -0.0390 0.3427 1.0000
7.750 1.3389 0.01357 0.00768 -0.0388 0.3386 1.0000
8.000 1.3620 0.01390 0.00797 -0.0384 0.3345 1.0000
8.250 1.3848 0.01425 0.00832 -0.0380 0.3306 1.0000
8.500 1.4079 0.01454 0.00866 -0.0376 0.3269 1.0000
8.750 1.4300 0.01488 0.00901 -0.0372 0.3230 1.0000
9.000 1.4508 0.01529 0.00940 -0.0366 0.3193 1.0000
9.250 1.4706 0.01576 0.00986 -0.0358 0.3156 1.0000
9.500 1.4909 0.01615 0.01031 -0.0352 0.3124 1.0000
9.750 1.5097 0.01659 0.01079 -0.0345 0.3088 1.0000
10.000 1.5262 0.01714 0.01134 -0.0335 0.3053 1.0000
10.250 1.5397 0.01782 0.01198 -0.0321 0.3016 1.0000
10.500 1.5527 0.01851 0.01274 -0.0310 0.2985 1.0000
10.750 1.5577 0.01948 0.01378 -0.0292 0.2955 1.0000
11.000 1.5554 0.02056 0.01490 -0.0263 0.2926 1.0000
11.250 1.5580 0.02169 0.01603 -0.0244 0.2897 1.0000
11.500 1.5633 0.02278 0.01708 -0.0227 0.2865 1.0000
11.750 1.5697 0.02394 0.01831 -0.0214 0.2839 1.0000
12.000 1.5753 0.02524 0.01968 -0.0204 0.2812 1.0000
12.250 1.5813 0.02656 0.02105 -0.0194 0.2784 1.0000
12.500 1.5871 0.02792 0.02242 -0.0185 0.2754 1.0000
12.750 1.5943 0.02915 0.02363 -0.0175 0.2725 1.0000
13.000 1.6034 0.03027 0.02476 -0.0166 0.2698 1.0000
13.250 1.6066 0.03202 0.02660 -0.0161 0.2674 1.0000
13.500 1.6106 0.03370 0.02836 -0.0155 0.2647 1.0000
13.750 1.6131 0.03553 0.03022 -0.0150 0.2613 1.0000
14.000 1.6180 0.03709 0.03175 -0.0144 0.2578 1.0000
14.250 1.6252 0.03848 0.03315 -0.0138 0.2547 1.0000
14.500 1.6245 0.04085 0.03563 -0.0137 0.2520 1.0000
14.750 1.6247 0.04318 0.03803 -0.0136 0.2487 1.0000
15.000 1.6298 0.04498 0.03987 -0.0134 0.2461 1.0000
15.250 1.6360 0.04662 0.04147 -0.0131 0.2428 1.0000
15.500 1.6406 0.04850 0.04339 -0.0130 0.2399 1.0000
15.750 1.6407 0.05099 0.04599 -0.0131 0.2375 1.0000
16.000 1.6394 0.05368 0.04876 -0.0132 0.2343 1.0000
16.250 1.6424 0.05586 0.05097 -0.0133 0.2316 1.0000
16.500 1.6486 0.05759 0.05271 -0.0132 0.2289 1.0000
16.750 1.6579 0.05895 0.05406 -0.0131 0.2262 1.0000
17.000 1.6538 0.06209 0.05734 -0.0135 0.2239 1.0000
17.250 1.6497 0.06526 0.06060 -0.0139 0.2209 1.0000
17.500 1.6491 0.06797 0.06336 -0.0143 0.2178 1.0000
17.750 1.6531 0.07006 0.06545 -0.0144 0.2150 1.0000
18.000 1.6574 0.07214 0.06754 -0.0146 0.2118 1.0000
18.250 1.6491 0.07595 0.07149 -0.0153 0.2091 1.0000
18.500 1.6445 0.07928 0.07491 -0.0159 0.2061 1.0000
18.750 1.6429 0.08223 0.07789 -0.0165 0.2029 1.0000
19.000 1.6492 0.08405 0.07965 -0.0167 0.1989 1.0000
19.250 1.6388 0.08827 0.08403 -0.0176 0.1964 1.0000
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