GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 448 AIRFOIL (goe448-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.59 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe448-il-1000000-n5.txt Download as CSV file: xf-goe448-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 448 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.1475 0.09309 0.08997 -0.1327 0.7174 0.0121
-9.750 0.1775 0.08160 0.07843 -0.1396 0.7024 0.0149
-9.500 0.1905 0.07987 0.07669 -0.1410 0.6988 0.0151
-9.250 0.2034 0.07813 0.07494 -0.1423 0.6948 0.0153
-7.750 0.2592 0.01449 0.00975 -0.2286 0.6741 0.0281
-7.500 0.2870 0.01359 0.00868 -0.2294 0.6709 0.0286
-7.250 0.3153 0.01293 0.00789 -0.2300 0.6675 0.0290
-7.000 0.3434 0.01241 0.00724 -0.2305 0.6637 0.0295
-6.750 0.3714 0.01200 0.00671 -0.2308 0.6599 0.0300
-6.250 0.4278 0.01132 0.00581 -0.2314 0.6536 0.0309
-6.000 0.4563 0.01105 0.00545 -0.2318 0.6501 0.0312
-5.750 0.4845 0.01078 0.00510 -0.2320 0.6463 0.0320
-5.500 0.5125 0.01057 0.00481 -0.2322 0.6426 0.0328
-5.250 0.5405 0.01038 0.00456 -0.2324 0.6395 0.0338
-5.000 0.5691 0.01020 0.00434 -0.2327 0.6366 0.0348
-4.750 0.5975 0.01005 0.00413 -0.2329 0.6331 0.0358
-4.500 0.6255 0.00993 0.00395 -0.2331 0.6293 0.0370
-4.250 0.6532 0.00985 0.00383 -0.2331 0.6257 0.0393
-4.000 0.6812 0.00977 0.00373 -0.2333 0.6228 0.0421
-3.750 0.7096 0.00980 0.00377 -0.2334 0.6199 0.0451
-3.500 0.7376 0.00979 0.00375 -0.2336 0.6164 0.0480
-3.250 0.7653 0.00986 0.00380 -0.2336 0.6127 0.0498
-3.000 0.7924 0.00999 0.00390 -0.2335 0.6091 0.0514
-2.750 0.8202 0.01000 0.00387 -0.2336 0.6063 0.0534
-2.500 0.8482 0.00994 0.00376 -0.2337 0.6033 0.0549
-2.250 0.8757 0.00996 0.00377 -0.2338 0.5998 0.0557
-2.000 0.9028 0.01005 0.00384 -0.2337 0.5961 0.0565
-1.750 0.9292 0.01015 0.00391 -0.2335 0.5926 0.0573
-1.500 0.9566 0.01021 0.00396 -0.2336 0.5896 0.0583
-1.250 0.9838 0.01024 0.00396 -0.2336 0.5855 0.0594
-1.000 1.0099 0.01025 0.00393 -0.2334 0.5804 0.0604
-0.750 1.0350 0.01034 0.00396 -0.2330 0.5749 0.0613
-0.500 1.0616 0.01039 0.00397 -0.2329 0.5696 0.0618
-0.250 1.0871 0.01035 0.00391 -0.2327 0.5640 0.0627
0.000 1.1117 0.01043 0.00396 -0.2323 0.5595 0.0635
0.250 1.1383 0.01042 0.00397 -0.2322 0.5561 0.0641
0.500 1.1641 0.01044 0.00398 -0.2320 0.5521 0.0646
0.750 1.1890 0.01049 0.00402 -0.2317 0.5478 0.0653
1.000 1.2130 0.01055 0.00405 -0.2311 0.5440 0.0657
1.250 1.2382 0.01056 0.00406 -0.2309 0.5409 0.0662
1.500 1.2619 0.01060 0.00409 -0.2303 0.5363 0.0666
1.750 1.2829 0.01068 0.00416 -0.2291 0.5306 0.0670
2.000 1.3039 0.01079 0.00424 -0.2280 0.5252 0.0674
2.250 1.3269 0.01087 0.00432 -0.2273 0.5199 0.0678
2.500 1.3495 0.01100 0.00445 -0.2266 0.5149 0.0682
2.750 1.3720 0.01117 0.00460 -0.2259 0.5103 0.0686
3.000 1.3961 0.01130 0.00474 -0.2255 0.5055 0.0690
3.250 1.4181 0.01151 0.00493 -0.2247 0.4995 0.0693
3.500 1.4399 0.01169 0.00511 -0.2239 0.4940 0.0701
3.750 1.4633 0.01184 0.00527 -0.2234 0.4889 0.0708
4.000 1.4848 0.01206 0.00550 -0.2226 0.4835 0.0714
4.250 1.5052 0.01234 0.00576 -0.2216 0.4784 0.0720
4.500 1.5275 0.01255 0.00599 -0.2210 0.4731 0.0726
4.750 1.5473 0.01286 0.00631 -0.2199 0.4667 0.0732
5.000 1.5666 0.01320 0.00664 -0.2188 0.4606 0.0738
5.250 1.5864 0.01354 0.00697 -0.2178 0.4533 0.0744
5.500 1.6032 0.01401 0.00742 -0.2163 0.4455 0.0751
5.750 1.6183 0.01457 0.00795 -0.2146 0.4333 0.0757
6.000 1.6327 0.01519 0.00854 -0.2128 0.4211 0.0764
6.250 1.6437 0.01600 0.00928 -0.2105 0.4054 0.0769
6.500 1.6531 0.01692 0.01013 -0.2080 0.3895 0.0774
6.750 1.6637 0.01782 0.01099 -0.2058 0.3763 0.0783
7.000 1.6734 0.01881 0.01192 -0.2035 0.3631 0.0802
7.250 1.6811 0.01993 0.01298 -0.2010 0.3494 0.0816
7.500 1.6887 0.02110 0.01411 -0.1986 0.3363 0.0832
7.750 1.6989 0.02215 0.01515 -0.1966 0.3254 0.0851
8.000 1.7057 0.02344 0.01640 -0.1942 0.3132 0.0872
8.500 1.7156 0.02644 0.01939 -0.1894 0.2868 0.1732
8.750 1.7193 0.02810 0.02104 -0.1869 0.2718 0.2087
9.000 1.7196 0.03016 0.02350 -0.1848 0.2466 0.6375
9.500 1.6712 0.03774 0.03119 -0.1744 0.1647 1.0000
9.750 1.6667 0.04044 0.03383 -0.1716 0.1485 1.0000
10.000 1.6668 0.04279 0.03615 -0.1694 0.1354 1.0000
10.250 1.6513 0.04660 0.03979 -0.1660 0.1047 1.0000
10.500 1.6217 0.05195 0.04494 -0.1616 0.0601 1.0000
10.750 1.6002 0.05673 0.04960 -0.1582 0.0198 1.0000
11.000 1.6035 0.05908 0.05197 -0.1568 0.0154 1.0000
11.250 1.6094 0.06115 0.05408 -0.1556 0.0138 1.0000
11.500 1.6149 0.06331 0.05628 -0.1545 0.0128 1.0000
11.750 1.6215 0.06536 0.05838 -0.1535 0.0121 1.0000
12.000 1.6266 0.06758 0.06064 -0.1524 0.0114 1.0000
12.250 1.6307 0.06991 0.06301 -0.1513 0.0107 1.0000
12.500 1.6344 0.07230 0.06545 -0.1502 0.0100 1.0000
12.750 1.6390 0.07462 0.06782 -0.1492 0.0097 1.0000
13.000 1.6439 0.07690 0.07015 -0.1483 0.0093 1.0000
13.250 1.6469 0.07945 0.07275 -0.1474 0.0089 1.0000
13.500 1.6509 0.08186 0.07521 -0.1465 0.0086 1.0000
13.750 1.6526 0.08457 0.07797 -0.1456 0.0082 1.0000
14.000 1.6547 0.08722 0.08066 -0.1447 0.0078 1.0000
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Polar data table (+)
Polar graphs
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