GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 50,000 Max Cl/Cd: 31.67 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe598-il-50000.txt Download as CSV file: xf-goe598-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 598 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4792 0.10106 0.09464 0.0065 1.0000 0.2541
-8.500 -0.4932 0.09853 0.09221 0.0054 1.0000 0.2641
-8.250 -0.6013 0.10423 0.09759 0.0159 1.0000 0.2525
-8.000 -0.5990 0.10073 0.09415 0.0157 1.0000 0.2661
-7.750 -0.5907 0.09687 0.09031 0.0164 1.0000 0.2820
-7.250 -0.5964 0.09113 0.08473 0.0160 1.0000 0.3181
-7.000 -0.5768 0.08654 0.08012 0.0186 1.0000 0.3400
-6.750 -0.5716 0.08323 0.07685 0.0201 1.0000 0.3655
-6.500 -0.5709 0.08070 0.07439 0.0220 1.0000 0.4002
-6.250 -0.5559 0.07728 0.07098 0.0260 1.0000 0.4405
-6.000 -0.5425 0.07362 0.06733 0.0287 1.0000 0.4739
-5.750 -0.5321 0.05147 0.04391 -0.0282 1.0000 0.1557
-5.500 -0.5085 0.04571 0.03758 -0.0301 1.0000 0.1354
-5.250 -0.4840 0.04101 0.03184 -0.0313 1.0000 0.1263
-5.000 -0.4604 0.03710 0.02755 -0.0311 1.0000 0.1251
-4.750 -0.4352 0.03351 0.02348 -0.0307 1.0000 0.1230
-4.500 -0.4085 0.03043 0.01983 -0.0301 1.0000 0.1236
-4.250 -0.3832 0.02805 0.01713 -0.0295 1.0000 0.1342
-4.000 -0.3560 0.02575 0.01443 -0.0287 1.0000 0.1426
-3.750 -0.3286 0.02375 0.01220 -0.0277 1.0000 0.1542
-3.500 -0.3028 0.02203 0.01056 -0.0267 1.0000 0.1814
-3.250 -0.2765 0.01991 0.00872 -0.0257 1.0000 0.2356
-3.000 -0.2678 0.01599 0.00753 -0.0208 1.0000 0.6262
-2.750 -0.1762 0.01528 0.00658 -0.0272 1.0000 1.0000
-2.500 -0.1597 0.01503 0.00597 -0.0260 1.0000 1.0000
-2.250 -0.1421 0.01485 0.00548 -0.0248 1.0000 1.0000
-2.000 -0.1236 0.01474 0.00508 -0.0236 1.0000 1.0000
-1.750 -0.1042 0.01466 0.00476 -0.0225 1.0000 1.0000
-1.500 -0.0842 0.01462 0.00445 -0.0214 1.0000 1.0000
-1.250 -0.0637 0.01461 0.00424 -0.0204 1.0000 1.0000
-1.000 -0.0429 0.01463 0.00410 -0.0195 1.0000 1.0000
-0.750 -0.0218 0.01467 0.00401 -0.0187 1.0000 1.0000
-0.500 -0.0007 0.01475 0.00397 -0.0178 1.0000 1.0000
-0.250 0.0204 0.01485 0.00396 -0.0171 1.0000 1.0000
0.000 0.0415 0.01499 0.00402 -0.0164 1.0000 1.0000
0.250 0.0627 0.01516 0.00414 -0.0157 1.0000 1.0000
0.500 0.0839 0.01537 0.00432 -0.0151 1.0000 1.0000
0.750 0.1050 0.01562 0.00456 -0.0146 1.0000 1.0000
1.000 0.1261 0.01591 0.00486 -0.0142 1.0000 1.0000
1.250 0.1471 0.01625 0.00521 -0.0138 1.0000 1.0000
1.500 0.1680 0.01662 0.00562 -0.0136 1.0000 1.0000
1.750 0.1889 0.01703 0.00609 -0.0134 1.0000 1.0000
2.000 0.2097 0.01749 0.00663 -0.0133 1.0000 1.0000
2.250 0.2304 0.01800 0.00727 -0.0132 1.0000 1.0000
2.500 0.2510 0.01855 0.00795 -0.0133 1.0000 1.0000
2.750 0.2714 0.01916 0.00870 -0.0134 1.0000 1.0000
3.000 0.2916 0.01982 0.00953 -0.0136 1.0000 1.0000
3.250 0.3115 0.02056 0.01045 -0.0138 1.0000 1.0000
3.500 0.3310 0.02137 0.01155 -0.0142 1.0000 1.0000
3.750 0.4162 0.02253 0.01341 -0.0265 0.9657 1.0000
4.000 0.5659 0.01787 0.01027 -0.0310 0.7366 1.0000
4.250 0.5537 0.02141 0.01026 -0.0188 0.1971 1.0000
4.500 0.5757 0.02422 0.01258 -0.0172 0.1410 1.0000
4.750 0.6026 0.02650 0.01464 -0.0160 0.1186 1.0000
5.000 0.6314 0.02873 0.01689 -0.0152 0.1054 1.0000
5.250 0.6614 0.03124 0.01983 -0.0141 0.1015 1.0000
5.500 0.6896 0.03419 0.02324 -0.0131 0.1003 1.0000
5.750 0.7154 0.03737 0.02702 -0.0121 0.0993 1.0000
6.000 0.7384 0.04063 0.03078 -0.0111 0.0971 1.0000
6.250 0.7591 0.04452 0.03527 -0.0101 0.0986 1.0000
6.500 0.7785 0.04914 0.04028 -0.0094 0.1035 1.0000
6.750 0.7941 0.05439 0.04636 -0.0088 0.1152 1.0000
7.000 0.8056 0.06101 0.05379 -0.0097 0.1378 1.0000
7.250 0.7421 0.05594 0.04963 -0.0061 0.1518 1.0000
8.000 0.7330 0.09977 0.09336 -0.0561 0.3724 1.0000
8.250 0.7542 0.10444 0.09805 -0.0538 0.3501 1.0000
8.500 0.7425 0.10709 0.10062 -0.0538 0.3297 1.0000
8.750 0.7531 0.11120 0.10478 -0.0525 0.3119 1.0000
9.000 0.6191 0.10750 0.10130 -0.0376 0.3230 1.0000
9.250 0.6161 0.11119 0.10495 -0.0372 0.3088 1.0000
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