GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 500,000 Max Cl/Cd: 117.99 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe497-il-500000.txt Download as CSV file: xf-goe497-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3154 0.13510 0.13263 -0.0437 1.0000 0.0353
-12.750 -0.5210 0.08473 0.08222 -0.0644 1.0000 0.0320
-12.500 -0.7223 0.04694 0.04386 -0.0967 0.9929 0.0304
-12.250 -0.7175 0.03702 0.03361 -0.1156 0.9834 0.0309
-12.000 -0.6936 0.03141 0.02760 -0.1284 0.9758 0.0316
-11.750 -0.6677 0.02801 0.02391 -0.1345 0.9721 0.0325
-11.500 -0.6356 0.02648 0.02234 -0.1379 0.9704 0.0334
-11.250 -0.6064 0.02536 0.02115 -0.1401 0.9670 0.0342
-11.000 -0.5778 0.02433 0.02001 -0.1420 0.9627 0.0353
-10.750 -0.5457 0.02317 0.01866 -0.1446 0.9601 0.0365
-10.500 -0.5122 0.02224 0.01752 -0.1470 0.9578 0.0373
-10.250 -0.4822 0.02033 0.01552 -0.1494 0.9556 0.0386
-10.000 -0.4581 0.01970 0.01487 -0.1493 0.9494 0.0396
-9.750 -0.4285 0.01901 0.01410 -0.1503 0.9451 0.0408
-9.500 -0.3976 0.01829 0.01325 -0.1515 0.9417 0.0421
-9.250 -0.3701 0.01768 0.01250 -0.1519 0.9369 0.0430
-9.000 -0.3462 0.01665 0.01136 -0.1518 0.9307 0.0442
-8.750 -0.3184 0.01592 0.01061 -0.1523 0.9263 0.0456
-8.500 -0.2910 0.01543 0.01006 -0.1525 0.9214 0.0469
-8.250 -0.2656 0.01494 0.00950 -0.1522 0.9151 0.0482
-8.000 -0.2376 0.01452 0.00896 -0.1523 0.9101 0.0496
-7.750 -0.2111 0.01390 0.00825 -0.1522 0.9049 0.0511
-7.500 -0.1860 0.01328 0.00762 -0.1519 0.8985 0.0529
-7.250 -0.1582 0.01288 0.00715 -0.1520 0.8931 0.0548
-7.000 -0.1315 0.01254 0.00675 -0.1517 0.8868 0.0568
-6.750 -0.1046 0.01221 0.00633 -0.1515 0.8803 0.0587
-6.500 -0.0769 0.01168 0.00576 -0.1516 0.8750 0.0620
-6.250 -0.0506 0.01139 0.00545 -0.1512 0.8680 0.0650
-6.000 -0.0231 0.01110 0.00507 -0.1510 0.8616 0.0682
-5.750 0.0047 0.01076 0.00474 -0.1510 0.8558 0.0734
-5.500 0.0319 0.01056 0.00449 -0.1508 0.8494 0.0785
-5.250 0.0600 0.01030 0.00423 -0.1508 0.8438 0.0861
-5.000 0.0876 0.01007 0.00399 -0.1506 0.8375 0.0944
-4.750 0.1151 0.00990 0.00379 -0.1504 0.8305 0.1034
-4.250 0.1706 0.00953 0.00342 -0.1502 0.8174 0.1235
-4.000 0.1987 0.00940 0.00324 -0.1500 0.8109 0.1324
-3.750 0.2266 0.00926 0.00310 -0.1499 0.8045 0.1429
-3.500 0.2541 0.00910 0.00297 -0.1498 0.7973 0.1543
-3.250 0.2824 0.00899 0.00283 -0.1497 0.7908 0.1676
-3.000 0.3096 0.00886 0.00275 -0.1494 0.7831 0.1834
-2.750 0.3377 0.00876 0.00266 -0.1493 0.7765 0.2019
-2.500 0.3654 0.00868 0.00261 -0.1492 0.7693 0.2207
-2.250 0.3932 0.00861 0.00255 -0.1490 0.7622 0.2383
-2.000 0.4212 0.00857 0.00252 -0.1489 0.7556 0.2555
-1.750 0.4488 0.00853 0.00250 -0.1487 0.7483 0.2729
-1.500 0.4769 0.00852 0.00246 -0.1485 0.7416 0.2875
-1.250 0.5042 0.00847 0.00245 -0.1483 0.7332 0.3006
-1.000 0.5319 0.00848 0.00241 -0.1480 0.7253 0.3142
-0.750 0.5591 0.00845 0.00241 -0.1478 0.7166 0.3274
-0.250 0.6141 0.00843 0.00242 -0.1473 0.7012 0.3537
0.000 0.6414 0.00846 0.00242 -0.1470 0.6935 0.3675
0.250 0.6686 0.00846 0.00245 -0.1467 0.6845 0.3827
0.500 0.6956 0.00851 0.00247 -0.1464 0.6758 0.3987
0.750 0.7225 0.00852 0.00252 -0.1460 0.6664 0.4149
1.000 0.7494 0.00857 0.00257 -0.1457 0.6581 0.4336
1.250 0.7762 0.00858 0.00264 -0.1453 0.6491 0.4535
1.500 0.8027 0.00863 0.00271 -0.1449 0.6401 0.4732
1.750 0.8289 0.00868 0.00278 -0.1445 0.6295 0.4922
2.000 0.8552 0.00872 0.00285 -0.1440 0.6191 0.5115
2.250 0.8810 0.00879 0.00293 -0.1435 0.6085 0.5335
2.500 0.9065 0.00881 0.00302 -0.1429 0.5962 0.5603
2.750 0.9317 0.00882 0.00313 -0.1423 0.5830 0.5965
3.000 0.9556 0.00877 0.00326 -0.1414 0.5686 0.6693
3.250 0.9794 0.00833 0.00337 -0.1403 0.5539 1.0000
3.500 1.0041 0.00851 0.00348 -0.1396 0.5376 1.0000
3.750 1.0282 0.00872 0.00360 -0.1388 0.5205 1.0000
4.000 1.0520 0.00896 0.00374 -0.1379 0.5041 1.0000
4.250 1.0758 0.00920 0.00391 -0.1371 0.4901 1.0000
4.500 1.0992 0.00947 0.00410 -0.1362 0.4780 1.0000
4.750 1.1222 0.00976 0.00430 -0.1352 0.4644 1.0000
5.000 1.1449 0.01005 0.00452 -0.1342 0.4500 1.0000
5.250 1.1680 0.01032 0.00475 -0.1333 0.4380 1.0000
5.500 1.1908 0.01061 0.00498 -0.1323 0.4285 1.0000
5.750 1.2142 0.01085 0.00521 -0.1315 0.4186 1.0000
6.000 1.2371 0.01112 0.00545 -0.1305 0.4092 1.0000
6.250 1.2595 0.01139 0.00570 -0.1295 0.3995 1.0000
6.500 1.2821 0.01162 0.00594 -0.1285 0.3892 1.0000
6.750 1.3031 0.01192 0.00620 -0.1272 0.3773 1.0000
7.000 1.3232 0.01222 0.00647 -0.1258 0.3637 1.0000
7.250 1.3426 0.01250 0.00673 -0.1242 0.3485 1.0000
7.500 1.3598 0.01284 0.00702 -0.1223 0.3309 1.0000
7.750 1.3755 0.01325 0.00737 -0.1201 0.3090 1.0000
8.000 1.3880 0.01381 0.00781 -0.1175 0.2863 1.0000
8.250 1.4005 0.01442 0.00831 -0.1149 0.2678 1.0000
8.500 1.4133 0.01503 0.00885 -0.1125 0.2532 1.0000
8.750 1.4265 0.01565 0.00942 -0.1102 0.2401 1.0000
9.000 1.4407 0.01625 0.00999 -0.1081 0.2281 1.0000
9.250 1.4547 0.01686 0.01058 -0.1060 0.2171 1.0000
9.500 1.4675 0.01755 0.01123 -0.1039 0.2051 1.0000
9.750 1.4801 0.01827 0.01192 -0.1018 0.1904 1.0000
10.000 1.4919 0.01907 0.01264 -0.0996 0.1682 1.0000
10.250 1.4948 0.02041 0.01375 -0.0965 0.1345 1.0000
10.500 1.4990 0.02174 0.01495 -0.0937 0.1160 1.0000
10.750 1.5056 0.02296 0.01613 -0.0913 0.1056 1.0000
11.000 1.5126 0.02421 0.01736 -0.0891 0.0982 1.0000
11.250 1.5223 0.02531 0.01849 -0.0872 0.0927 1.0000
11.500 1.5305 0.02655 0.01974 -0.0853 0.0876 1.0000
11.750 1.5375 0.02791 0.02113 -0.0834 0.0835 1.0000
12.000 1.5488 0.02900 0.02228 -0.0819 0.0802 1.0000
12.250 1.5572 0.03033 0.02364 -0.0803 0.0767 1.0000
12.500 1.5618 0.03201 0.02534 -0.0786 0.0732 1.0000
12.750 1.5729 0.03321 0.02662 -0.0774 0.0707 1.0000
13.000 1.5818 0.03462 0.02807 -0.0761 0.0677 1.0000
13.250 1.5875 0.03634 0.02983 -0.0748 0.0647 1.0000
13.500 1.5932 0.03814 0.03168 -0.0735 0.0619 1.0000
13.750 1.6027 0.03961 0.03323 -0.0726 0.0588 1.0000
14.000 1.6077 0.04158 0.03521 -0.0715 0.0554 1.0000
14.250 1.6139 0.04348 0.03718 -0.0706 0.0518 1.0000
14.500 1.6181 0.04564 0.03936 -0.0698 0.0472 1.0000
14.750 1.6221 0.04789 0.04164 -0.0691 0.0422 1.0000
15.000 1.6221 0.05065 0.04441 -0.0684 0.0365 1.0000
15.250 1.6202 0.05373 0.04751 -0.0679 0.0319 1.0000
15.500 1.6169 0.05708 0.05090 -0.0675 0.0286 1.0000
15.750 1.6142 0.06047 0.05436 -0.0673 0.0264 1.0000
16.000 1.6098 0.06419 0.05814 -0.0673 0.0247 1.0000
16.250 1.6033 0.06831 0.06233 -0.0676 0.0235 1.0000
16.500 1.6004 0.07206 0.06619 -0.0680 0.0225 1.0000
16.750 1.5959 0.07614 0.07038 -0.0686 0.0217 1.0000
17.000 1.5892 0.08065 0.07498 -0.0694 0.0210 1.0000
17.250 1.5800 0.08570 0.08012 -0.0706 0.0204 1.0000
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