GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 100,000 Max Cl/Cd: 55.15 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe488-il-100000.txt Download as CSV file: xf-goe488-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4138 0.10157 0.09653 -0.0267 1.0000 0.0832
-8.250 -0.4313 0.10086 0.09596 -0.0286 1.0000 0.0838
-8.000 -0.4418 0.09937 0.09453 -0.0328 1.0000 0.0841
-7.750 -0.4117 0.09160 0.08673 -0.0250 1.0000 0.0875
-7.500 -0.4096 0.08905 0.08422 -0.0236 1.0000 0.0909
-7.250 -0.4149 0.08682 0.08206 -0.0235 1.0000 0.0940
-7.000 -0.4241 0.08504 0.08036 -0.0267 1.0000 0.0971
-6.750 -0.4352 0.08443 0.07965 -0.0343 1.0000 0.0985
-6.500 -0.4259 0.07856 0.07394 -0.0259 1.0000 0.1011
-6.250 -0.4224 0.07595 0.07136 -0.0237 1.0000 0.1039
-6.000 -0.4205 0.07342 0.06883 -0.0236 1.0000 0.1080
-5.750 -0.4176 0.07076 0.06598 -0.0300 1.0000 0.1136
-5.500 -0.4134 0.06725 0.06258 -0.0258 1.0000 0.1156
-5.250 -0.4071 0.06473 0.06008 -0.0239 1.0000 0.1197
-5.000 -0.3949 0.06174 0.05687 -0.0277 1.0000 0.1288
-4.750 -0.3887 0.05905 0.05428 -0.0244 1.0000 0.1330
-4.500 -0.3729 0.05628 0.05127 -0.0270 1.0000 0.1437
-4.250 -0.3537 0.05532 0.04997 -0.0286 1.0000 0.1569
-4.000 -0.3464 0.05091 0.04575 -0.0261 1.0000 0.1592
-3.750 -0.3325 0.04865 0.04347 -0.0250 1.0000 0.1673
-3.500 -0.3163 0.04601 0.04073 -0.0250 1.0000 0.1770
-3.250 -0.2993 0.04380 0.03842 -0.0248 1.0000 0.1913
-3.000 -0.2824 0.04173 0.03628 -0.0243 1.0000 0.2076
-2.750 -0.2641 0.03972 0.03416 -0.0239 1.0000 0.2234
-2.500 -0.2439 0.03799 0.03225 -0.0241 1.0000 0.2472
-2.250 -0.1819 0.03143 0.02392 -0.0289 1.0000 0.1272
-2.000 -0.1551 0.02785 0.02001 -0.0288 1.0000 0.1100
-1.750 -0.1311 0.02615 0.01801 -0.0282 1.0000 0.1084
-1.500 -0.1070 0.02466 0.01621 -0.0275 1.0000 0.1067
-1.250 -0.0823 0.02322 0.01437 -0.0267 1.0000 0.1033
-1.000 -0.0585 0.02220 0.01303 -0.0259 1.0000 0.1021
-0.750 -0.0357 0.02145 0.01214 -0.0250 1.0000 0.1025
-0.500 -0.0136 0.02088 0.01149 -0.0242 1.0000 0.1042
-0.250 0.0368 0.02049 0.01100 -0.0286 0.9903 0.1103
0.000 0.0863 0.02009 0.01070 -0.0329 0.9797 0.1220
0.250 0.1338 0.01965 0.01039 -0.0366 0.9707 0.1384
0.500 0.1939 0.01664 0.00998 -0.0426 0.9677 1.0000
0.750 0.2414 0.01694 0.00992 -0.0465 0.9572 1.0000
1.000 0.2837 0.01711 0.00993 -0.0493 0.9452 1.0000
1.250 0.3270 0.01722 0.00994 -0.0523 0.9332 1.0000
1.500 0.3722 0.01723 0.00988 -0.0554 0.9209 1.0000
1.750 0.4198 0.01712 0.00975 -0.0589 0.9090 1.0000
2.000 0.4747 0.01680 0.00944 -0.0634 0.8985 1.0000
2.250 0.5229 0.01635 0.00904 -0.0665 0.8846 1.0000
2.500 0.5690 0.01580 0.00856 -0.0689 0.8697 1.0000
2.750 0.6045 0.01530 0.00814 -0.0690 0.8489 1.0000
3.000 0.6470 0.01454 0.00746 -0.0700 0.8261 1.0000
3.250 0.6758 0.01396 0.00690 -0.0684 0.7885 1.0000
3.500 0.7043 0.01349 0.00636 -0.0667 0.7347 1.0000
3.750 0.7326 0.01333 0.00592 -0.0652 0.6615 1.0000
4.000 0.7578 0.01374 0.00590 -0.0637 0.5941 1.0000
4.250 0.7798 0.01434 0.00619 -0.0621 0.5450 1.0000
4.500 0.8020 0.01491 0.00656 -0.0608 0.5096 1.0000
4.750 0.8245 0.01548 0.00698 -0.0595 0.4812 1.0000
5.000 0.8468 0.01608 0.00746 -0.0583 0.4553 1.0000
5.250 0.8691 0.01671 0.00795 -0.0572 0.4311 1.0000
5.500 0.8908 0.01732 0.00851 -0.0559 0.4067 1.0000
5.750 0.9130 0.01799 0.00911 -0.0548 0.3850 1.0000
6.000 0.9347 0.01863 0.00977 -0.0537 0.3629 1.0000
6.250 0.9546 0.01919 0.01033 -0.0522 0.3383 1.0000
6.500 0.9733 0.01967 0.01075 -0.0505 0.3131 1.0000
6.750 0.9921 0.02006 0.01126 -0.0488 0.2893 1.0000
7.000 1.0101 0.02035 0.01169 -0.0470 0.2643 1.0000
7.250 1.0273 0.02054 0.01199 -0.0451 0.2339 1.0000
7.500 1.0434 0.02092 0.01234 -0.0431 0.1902 1.0000
7.750 1.0496 0.02297 0.01369 -0.0400 0.1008 1.0000
8.000 1.0590 0.02502 0.01546 -0.0370 0.0704 1.0000
8.250 1.0696 0.02684 0.01726 -0.0342 0.0624 1.0000
8.500 1.0826 0.02860 0.01906 -0.0319 0.0574 1.0000
8.750 1.0994 0.03093 0.02137 -0.0303 0.0534 1.0000
9.000 1.1185 0.03264 0.02328 -0.0288 0.0494 1.0000
9.250 1.1388 0.03478 0.02552 -0.0277 0.0468 1.0000
9.500 1.1603 0.03743 0.02829 -0.0269 0.0452 1.0000
9.750 1.1811 0.04085 0.03190 -0.0262 0.0442 1.0000
10.000 1.1968 0.04462 0.03599 -0.0248 0.0438 1.0000
10.250 1.2066 0.04814 0.03993 -0.0228 0.0437 1.0000
10.500 1.2109 0.05199 0.04417 -0.0205 0.0435 1.0000
10.750 1.2083 0.05631 0.04885 -0.0178 0.0433 1.0000
11.000 1.2016 0.05920 0.05212 -0.0146 0.0431 1.0000
11.250 1.1909 0.06234 0.05559 -0.0113 0.0430 1.0000
11.500 1.1754 0.06548 0.05899 -0.0079 0.0430 1.0000
11.750 1.1599 0.06951 0.06324 -0.0055 0.0432 1.0000
12.000 1.1464 0.07284 0.06681 -0.0037 0.0435 1.0000
12.250 1.1262 0.07644 0.07062 -0.0028 0.0436 1.0000
12.500 1.1040 0.08055 0.07495 -0.0032 0.0439 1.0000
12.750 0.8953 0.09493 0.09025 -0.0129 0.0499 1.0000
13.000 0.8496 0.10785 0.10326 -0.0213 0.0516 1.0000
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Polar data table (+)
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