GOE 741 AIRFOIL (goe741-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 741 AIRFOIL (goe741-il) Reynolds number: 500,000 Max Cl/Cd: 101.44 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe741-il-500000.txt Download as CSV file: xf-goe741-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 741 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3313 0.09605 0.09230 -0.0108 0.5802 0.0444
-9.500 -0.5864 0.04995 0.04595 -0.0349 0.5953 0.0388
-9.250 -0.5822 0.04761 0.04349 -0.0336 0.5907 0.0383
-9.000 -0.5963 0.04279 0.03845 -0.0316 0.5877 0.0380
-8.750 -0.6126 0.03716 0.03239 -0.0287 0.5848 0.0376
-8.500 -0.6193 0.03238 0.02711 -0.0257 0.5814 0.0372
-8.250 -0.6133 0.02920 0.02349 -0.0233 0.5776 0.0372
-8.000 -0.6005 0.02693 0.02084 -0.0213 0.5736 0.0372
-7.750 -0.5832 0.02520 0.01882 -0.0198 0.5697 0.0374
-7.500 -0.5632 0.02377 0.01714 -0.0185 0.5657 0.0376
-7.250 -0.5417 0.02258 0.01573 -0.0174 0.5616 0.0379
-7.000 -0.5188 0.02160 0.01452 -0.0164 0.5578 0.0381
-6.750 -0.4950 0.02084 0.01354 -0.0155 0.5540 0.0384
-6.500 -0.4706 0.01995 0.01248 -0.0148 0.5508 0.0387
-6.250 -0.4457 0.01880 0.01130 -0.0142 0.5476 0.0393
-6.000 -0.4197 0.01820 0.01067 -0.0137 0.5441 0.0398
-5.750 -0.3935 0.01769 0.01011 -0.0132 0.5406 0.0404
-5.500 -0.3671 0.01718 0.00950 -0.0127 0.5372 0.0410
-5.250 -0.3407 0.01675 0.00896 -0.0122 0.5336 0.0415
-5.000 -0.3136 0.01626 0.00843 -0.0118 0.5312 0.0421
-4.750 -0.2865 0.01582 0.00794 -0.0114 0.5284 0.0427
-4.500 -0.2592 0.01546 0.00752 -0.0110 0.5254 0.0433
-4.250 -0.2327 0.01487 0.00689 -0.0105 0.5224 0.0441
-4.000 -0.2061 0.01445 0.00647 -0.0101 0.5194 0.0450
-3.750 -0.1792 0.01420 0.00618 -0.0097 0.5163 0.0461
-3.500 -0.1519 0.01397 0.00593 -0.0093 0.5136 0.0474
-3.250 -0.1241 0.01375 0.00568 -0.0090 0.5113 0.0487
-3.000 -0.0976 0.01334 0.00531 -0.0085 0.5087 0.0506
-2.750 -0.0703 0.01310 0.00509 -0.0082 0.5058 0.0525
-2.500 -0.0427 0.01291 0.00485 -0.0078 0.5029 0.0547
-2.250 -0.0159 0.01262 0.00459 -0.0074 0.5003 0.0581
-2.000 0.0112 0.01248 0.00442 -0.0070 0.4975 0.0627
-1.750 0.0384 0.01234 0.00433 -0.0067 0.4950 0.0705
-1.500 0.0660 0.01216 0.00425 -0.0064 0.4928 0.0836
-1.250 0.0938 0.01204 0.00418 -0.0062 0.4901 0.0980
-1.000 0.1214 0.01191 0.00408 -0.0059 0.4872 0.1098
-0.750 0.1487 0.01177 0.00398 -0.0056 0.4847 0.1210
-0.500 0.1759 0.01165 0.00390 -0.0053 0.4822 0.1337
-0.250 0.2031 0.01160 0.00389 -0.0050 0.4795 0.1516
0.000 0.2303 0.01158 0.00397 -0.0048 0.4766 0.1793
0.250 0.2582 0.01152 0.00398 -0.0046 0.4743 0.2024
0.500 0.2860 0.01145 0.00398 -0.0044 0.4715 0.2213
0.750 0.3135 0.01136 0.00394 -0.0042 0.4681 0.2402
1.000 0.3407 0.01124 0.00386 -0.0039 0.4645 0.2608
1.250 0.3674 0.01118 0.00384 -0.0036 0.4608 0.2846
1.500 0.3937 0.01107 0.00386 -0.0032 0.4577 0.3208
1.750 0.4084 0.01017 0.00381 -0.0008 0.4552 0.5810
2.000 0.4595 0.00954 0.00426 -0.0045 0.4515 0.9393
2.250 0.5132 0.00989 0.00455 -0.0092 0.4481 0.9561
2.500 0.5580 0.01020 0.00478 -0.0122 0.4450 0.9673
2.750 0.6218 0.01050 0.00497 -0.0193 0.4412 0.9732
3.000 0.6622 0.01067 0.00515 -0.0217 0.4382 0.9807
3.250 0.7254 0.01068 0.00514 -0.0288 0.4341 0.9863
3.500 0.7712 0.01073 0.00514 -0.0323 0.4303 0.9922
3.750 0.8342 0.01056 0.00488 -0.0396 0.4259 0.9995
4.000 0.8633 0.01061 0.00493 -0.0399 0.4226 1.0000
4.250 0.8893 0.01065 0.00499 -0.0396 0.4191 1.0000
4.500 0.9152 0.01070 0.00504 -0.0392 0.4155 1.0000
4.750 0.9409 0.01076 0.00508 -0.0388 0.4120 1.0000
5.000 0.9663 0.01090 0.00515 -0.0384 0.4082 1.0000
5.250 0.9920 0.01096 0.00527 -0.0381 0.4047 1.0000
5.500 1.0176 0.01103 0.00536 -0.0377 0.4006 1.0000
5.750 1.0430 0.01110 0.00542 -0.0373 0.3961 1.0000
6.000 1.0678 0.01125 0.00551 -0.0369 0.3915 1.0000
6.250 1.0932 0.01132 0.00565 -0.0365 0.3867 1.0000
6.500 1.1182 0.01142 0.00576 -0.0361 0.3815 1.0000
6.750 1.1426 0.01158 0.00587 -0.0357 0.3763 1.0000
7.000 1.1672 0.01171 0.00604 -0.0352 0.3711 1.0000
7.250 1.1916 0.01185 0.00619 -0.0348 0.3648 1.0000
7.500 1.2148 0.01208 0.00637 -0.0342 0.3590 1.0000
7.750 1.2389 0.01223 0.00658 -0.0337 0.3532 1.0000
8.000 1.2619 0.01244 0.00679 -0.0331 0.3466 1.0000
8.250 1.2843 0.01270 0.00704 -0.0324 0.3405 1.0000
8.500 1.3067 0.01293 0.00730 -0.0317 0.3341 1.0000
8.750 1.3274 0.01327 0.00760 -0.0308 0.3277 1.0000
9.000 1.3487 0.01354 0.00792 -0.0300 0.3216 1.0000
9.250 1.3684 0.01389 0.00826 -0.0290 0.3150 1.0000
9.500 1.3868 0.01428 0.00865 -0.0278 0.3085 1.0000
9.750 1.4046 0.01466 0.00904 -0.0265 0.3011 1.0000
10.000 1.4190 0.01518 0.00953 -0.0248 0.2948 1.0000
10.250 1.4352 0.01556 0.00996 -0.0233 0.2895 1.0000
10.500 1.4472 0.01608 0.01048 -0.0213 0.2842 1.0000
10.750 1.4546 0.01673 0.01111 -0.0186 0.2795 1.0000
11.000 1.4640 0.01722 0.01167 -0.0162 0.2754 1.0000
11.250 1.4608 0.01791 0.01240 -0.0120 0.2719 1.0000
11.500 1.4511 0.01895 0.01345 -0.0076 0.2687 1.0000
11.750 1.4476 0.02021 0.01469 -0.0047 0.2649 1.0000
12.000 1.4538 0.02119 0.01574 -0.0029 0.2615 1.0000
12.250 1.4593 0.02233 0.01693 -0.0014 0.2576 1.0000
12.500 1.4633 0.02364 0.01826 0.0001 0.2540 1.0000
12.750 1.4651 0.02517 0.01977 0.0015 0.2501 1.0000
13.000 1.4719 0.02646 0.02113 0.0025 0.2467 1.0000
13.250 1.4787 0.02782 0.02255 0.0034 0.2433 1.0000
13.500 1.4834 0.02934 0.02411 0.0043 0.2399 1.0000
13.750 1.4856 0.03109 0.02586 0.0051 0.2362 1.0000
14.000 1.4895 0.03275 0.02756 0.0059 0.2325 1.0000
14.250 1.4938 0.03452 0.02941 0.0063 0.2285 1.0000
14.500 1.4949 0.03654 0.03146 0.0069 0.2241 1.0000
14.750 1.4937 0.03873 0.03363 0.0075 0.2196 1.0000
15.000 1.4978 0.04069 0.03569 0.0076 0.2157 1.0000
15.250 1.4997 0.04288 0.03794 0.0078 0.2114 1.0000
15.500 1.4982 0.04541 0.04046 0.0080 0.2066 1.0000
15.750 1.4996 0.04770 0.04281 0.0080 0.2023 1.0000
16.000 1.5004 0.05016 0.04534 0.0080 0.1975 1.0000
16.250 1.4968 0.05305 0.04824 0.0079 0.1919 1.0000
16.500 1.4967 0.05567 0.05091 0.0077 0.1872 1.0000
16.750 1.4945 0.05854 0.05384 0.0075 0.1812 1.0000
17.000 1.4891 0.06178 0.05708 0.0072 0.1753 1.0000
17.250 1.4850 0.06499 0.06034 0.0067 0.1680 1.0000
17.500 1.4781 0.06850 0.06385 0.0063 0.1616 1.0000
17.750 1.4714 0.07206 0.06744 0.0058 0.1543 1.0000
18.000 1.4623 0.07594 0.07134 0.0051 0.1480 1.0000
18.250 1.4541 0.07977 0.07517 0.0044 0.1414 1.0000
18.500 1.4439 0.08389 0.07930 0.0036 0.1359 1.0000
18.750 1.4362 0.08772 0.08315 0.0028 0.1303 1.0000
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