GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 448 AIRFOIL (goe448-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.1 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe448-il-1000000.txt Download as CSV file: xf-goe448-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.1963 0.09795 0.09506 -0.1319 0.7541 0.0193
-10.000 0.1981 0.09370 0.09077 -0.1349 0.7499 0.0207
-9.750 0.2035 0.09009 0.08717 -0.1367 0.7464 0.0209
-9.500 0.2175 0.08840 0.08547 -0.1371 0.7423 0.0211
-9.250 0.2306 0.08675 0.08380 -0.1380 0.7380 0.0214
-9.000 0.2427 0.08495 0.08196 -0.1392 0.7336 0.0219
-8.750 0.2544 0.08286 0.07987 -0.1405 0.7300 0.0226
-8.500 0.2569 0.07876 0.07578 -0.1444 0.7260 0.0245
-7.000 0.3338 0.01438 0.00987 -0.2278 0.7035 0.0334
-6.750 0.3615 0.01288 0.00804 -0.2290 0.6998 0.0341
-6.500 0.3900 0.01220 0.00726 -0.2296 0.6966 0.0351
-6.250 0.4184 0.01183 0.00680 -0.2300 0.6929 0.0359
-6.000 0.4466 0.01150 0.00637 -0.2302 0.6891 0.0367
-5.750 0.4745 0.01124 0.00597 -0.2305 0.6850 0.0377
-5.500 0.5032 0.01090 0.00554 -0.2308 0.6820 0.0386
-5.250 0.5318 0.01050 0.00505 -0.2312 0.6786 0.0399
-5.000 0.5602 0.01038 0.00490 -0.2314 0.6749 0.0413
-4.750 0.5882 0.01032 0.00478 -0.2315 0.6712 0.0427
-4.500 0.6165 0.01019 0.00457 -0.2316 0.6676 0.0443
-4.250 0.6452 0.01014 0.00452 -0.2318 0.6644 0.0463
-4.000 0.6737 0.01031 0.00472 -0.2319 0.6609 0.0479
-3.750 0.7017 0.01044 0.00482 -0.2319 0.6573 0.0499
-3.500 0.7294 0.01052 0.00482 -0.2320 0.6534 0.0518
-3.250 0.7578 0.01075 0.00510 -0.2320 0.6503 0.0528
-3.000 0.7860 0.01098 0.00536 -0.2321 0.6469 0.0538
-2.750 0.8139 0.01113 0.00549 -0.2321 0.6435 0.0555
-2.500 0.8413 0.01123 0.00550 -0.2321 0.6399 0.0575
-2.250 0.8688 0.01112 0.00532 -0.2322 0.6363 0.0590
-2.000 0.8966 0.01115 0.00539 -0.2324 0.6332 0.0600
-1.750 0.9241 0.01125 0.00551 -0.2324 0.6298 0.0612
-1.500 0.9511 0.01132 0.00556 -0.2324 0.6262 0.0628
-1.250 0.9776 0.01136 0.00551 -0.2323 0.6219 0.0645
-1.000 1.0049 0.01140 0.00552 -0.2323 0.6180 0.0657
-0.750 1.0322 0.01102 0.00506 -0.2325 0.6134 0.0675
-0.500 1.0580 0.01094 0.00496 -0.2323 0.6086 0.0689
-0.250 1.0839 0.01096 0.00497 -0.2322 0.6042 0.0705
0.000 1.1111 0.01092 0.00493 -0.2322 0.6008 0.0723
0.250 1.1377 0.01086 0.00484 -0.2322 0.5970 0.0736
0.500 1.1637 0.01082 0.00475 -0.2320 0.5932 0.0743
0.750 1.1888 0.01090 0.00476 -0.2316 0.5894 0.0750
1.000 1.2155 0.01095 0.00481 -0.2316 0.5865 0.0758
1.250 1.2423 0.01070 0.00454 -0.2317 0.5830 0.0761
1.500 1.2682 0.01054 0.00436 -0.2316 0.5791 0.0766
1.750 1.2928 0.01048 0.00428 -0.2312 0.5751 0.0772
2.000 1.3183 0.01043 0.00424 -0.2310 0.5714 0.0779
2.250 1.3440 0.01039 0.00423 -0.2308 0.5673 0.0787
2.500 1.3678 0.01044 0.00427 -0.2303 0.5624 0.0800
2.750 1.3883 0.01055 0.00435 -0.2291 0.5572 0.0807
3.000 1.4122 0.01055 0.00439 -0.2285 0.5532 0.0814
3.250 1.4345 0.01061 0.00446 -0.2277 0.5491 0.0821
3.500 1.4561 0.01074 0.00457 -0.2267 0.5449 0.0826
3.750 1.4782 0.01089 0.00472 -0.2259 0.5407 0.0832
4.000 1.5029 0.01098 0.00484 -0.2256 0.5367 0.0838
4.250 1.5259 0.01113 0.00499 -0.2250 0.5320 0.0844
4.500 1.5467 0.01135 0.00520 -0.2240 0.5271 0.0850
4.750 1.5696 0.01152 0.00539 -0.2235 0.5229 0.0857
5.000 1.5924 0.01169 0.00558 -0.2229 0.5183 0.0865
5.250 1.6131 0.01193 0.00581 -0.2219 0.5132 0.0889
5.500 1.6330 0.01220 0.00610 -0.2208 0.5071 0.0911
5.750 1.6528 0.01249 0.00639 -0.2198 0.4994 0.0936
6.000 1.6701 0.01288 0.00677 -0.2183 0.4912 0.0964
6.250 1.6879 0.01327 0.00716 -0.2169 0.4823 0.1047
6.500 1.7060 0.01365 0.00765 -0.2157 0.4741 0.1856
6.750 1.7208 0.01419 0.00826 -0.2140 0.4636 0.2648
7.000 1.7394 0.01390 0.00899 -0.2132 0.4531 1.0000
7.250 1.7526 0.01459 0.00964 -0.2112 0.4423 1.0000
7.500 1.7634 0.01542 0.01041 -0.2089 0.4290 1.0000
7.750 1.7732 0.01634 0.01126 -0.2065 0.4155 1.0000
8.000 1.7816 0.01738 0.01223 -0.2040 0.4004 1.0000
8.500 1.7913 0.01998 0.01468 -0.1982 0.3669 1.0000
8.750 1.7948 0.02145 0.01607 -0.1953 0.3505 1.0000
9.000 1.7971 0.02304 0.01759 -0.1924 0.3346 1.0000
9.250 1.7984 0.02477 0.01925 -0.1894 0.3185 1.0000
9.500 1.7978 0.02671 0.02111 -0.1864 0.3004 1.0000
9.750 1.7905 0.02921 0.02348 -0.1827 0.2768 1.0000
10.000 1.7774 0.03225 0.02635 -0.1785 0.2463 1.0000
10.250 1.7493 0.03668 0.03052 -0.1731 0.2009 1.0000
10.500 1.7231 0.04117 0.03482 -0.1683 0.1650 1.0000
10.750 1.7107 0.04466 0.03821 -0.1650 0.1437 1.0000
11.000 1.6952 0.04851 0.04191 -0.1617 0.1160 1.0000
11.250 1.6663 0.05383 0.04702 -0.1576 0.0743 1.0000
11.500 1.6365 0.05952 0.05255 -0.1537 0.0336 1.0000
11.750 1.6287 0.06306 0.05608 -0.1517 0.0177 1.0000
12.000 1.6322 0.06544 0.05851 -0.1504 0.0163 1.0000
12.250 1.6347 0.06796 0.06108 -0.1492 0.0151 1.0000
12.500 1.6376 0.07044 0.06362 -0.1480 0.0143 1.0000
12.750 1.6413 0.07284 0.06608 -0.1470 0.0139 1.0000
13.000 1.6440 0.07539 0.06869 -0.1459 0.0134 1.0000
13.250 1.6459 0.07803 0.07140 -0.1449 0.0130 1.0000
13.500 1.6466 0.08086 0.07428 -0.1438 0.0125 1.0000
13.750 1.6448 0.08402 0.07752 -0.1428 0.0119 1.0000
14.000 1.6421 0.08727 0.08085 -0.1417 0.0115 1.0000
14.250 1.6437 0.09004 0.08368 -0.1409 0.0113 1.0000
14.500 1.6454 0.09279 0.08650 -0.1401 0.0111 1.0000
14.750 1.6456 0.09578 0.08956 -0.1394 0.0108 1.0000
15.000 1.6460 0.09874 0.09258 -0.1388 0.0105 1.0000
15.250 1.6453 0.10188 0.09579 -0.1382 0.0103 1.0000
15.500 1.6447 0.10499 0.09895 -0.1376 0.0100 1.0000
15.750 1.6425 0.10833 0.10237 -0.1372 0.0098 1.0000
16.000 1.6401 0.11171 0.10582 -0.1367 0.0096 1.0000
16.250 1.6348 0.11556 0.10974 -0.1364 0.0094 1.0000
16.500 1.6245 0.12014 0.11443 -0.1362 0.0091 1.0000
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