GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 500,000 Max Cl/Cd: 96.7 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe509-il-500000.txt Download as CSV file: xf-goe509-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 509 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2640 0.08839 0.08624 -0.0489 0.9897 0.0261
-8.500 -0.2602 0.08016 0.07802 -0.0625 0.9849 0.0274
-8.250 -0.2613 0.07335 0.07121 -0.0693 0.9779 0.0278
-8.000 -0.2426 0.06867 0.06650 -0.0746 0.9740 0.0279
-7.750 -0.2179 0.06567 0.06347 -0.0785 0.9721 0.0284
-7.500 -0.2627 0.03382 0.03073 -0.0948 0.9583 0.0227
-7.250 -0.2778 0.02529 0.02127 -0.0911 0.9465 0.0229
-7.000 -0.2585 0.02298 0.01873 -0.0904 0.9406 0.0235
-6.750 -0.2311 0.02309 0.01892 -0.0903 0.9336 0.0242
-6.500 -0.2053 0.02110 0.01662 -0.0904 0.9290 0.0251
-6.250 -0.1943 0.01931 0.01449 -0.0870 0.9152 0.0261
-6.000 -0.1769 0.01821 0.01304 -0.0845 0.9001 0.0274
-5.750 -0.1555 0.01657 0.01121 -0.0834 0.8856 0.0286
-5.500 -0.1243 0.01604 0.01061 -0.0840 0.8717 0.0299
-5.250 -0.0926 0.01518 0.00952 -0.0846 0.8569 0.0314
-5.000 -0.0622 0.01470 0.00875 -0.0848 0.8417 0.0330
-4.750 -0.0359 0.01362 0.00752 -0.0846 0.8278 0.0349
-4.500 -0.0095 0.01336 0.00716 -0.0842 0.8154 0.0366
-4.250 0.0166 0.01298 0.00663 -0.0836 0.8046 0.0383
-4.000 0.0427 0.01278 0.00627 -0.0830 0.7940 0.0398
-3.750 0.0667 0.01201 0.00545 -0.0821 0.7837 0.0422
-3.500 0.0921 0.01180 0.00518 -0.0815 0.7742 0.0443
-3.250 0.1170 0.01155 0.00487 -0.0807 0.7645 0.0463
-3.000 0.1425 0.01141 0.00464 -0.0799 0.7558 0.0481
-2.750 0.1661 0.01082 0.00401 -0.0789 0.7468 0.0508
-2.500 0.1905 0.01060 0.00377 -0.0781 0.7377 0.0534
-2.000 0.2397 0.01032 0.00339 -0.0763 0.7181 0.0586
-1.750 0.2622 0.00996 0.00302 -0.0750 0.7073 0.0637
-1.500 0.2860 0.00986 0.00286 -0.0740 0.6955 0.0686
-1.250 0.3085 0.00967 0.00265 -0.0726 0.6813 0.0766
-1.000 0.3308 0.00956 0.00249 -0.0713 0.6648 0.0874
-0.750 0.3515 0.00938 0.00234 -0.0696 0.6450 0.1139
-0.500 0.3684 0.00906 0.00236 -0.0674 0.6214 0.2419
-0.250 0.3886 0.00913 0.00238 -0.0656 0.5918 0.2780
0.000 0.4077 0.00928 0.00239 -0.0636 0.5555 0.2966
0.250 0.4262 0.00948 0.00242 -0.0616 0.5177 0.3118
1.000 0.4883 0.00990 0.00259 -0.0570 0.4639 0.3581
1.250 0.5100 0.00997 0.00265 -0.0558 0.4547 0.3755
1.750 0.5411 0.00945 0.00270 -0.0507 0.4420 0.6028
2.250 0.7589 0.00996 0.00391 -0.0863 0.4212 0.9890
2.500 0.8026 0.01017 0.00405 -0.0898 0.4148 0.9941
2.750 0.8476 0.01030 0.00410 -0.0938 0.4093 0.9978
3.000 0.8855 0.01033 0.00414 -0.0961 0.4043 1.0000
3.250 0.9064 0.01045 0.00422 -0.0948 0.3997 1.0000
3.500 0.9265 0.01064 0.00435 -0.0933 0.3943 1.0000
3.750 0.9483 0.01070 0.00444 -0.0921 0.3902 1.0000
4.000 0.9695 0.01079 0.00453 -0.0907 0.3843 1.0000
4.250 0.9899 0.01094 0.00465 -0.0893 0.3796 1.0000
4.500 1.0111 0.01104 0.00476 -0.0880 0.3740 1.0000
4.750 1.0324 0.01113 0.00488 -0.0867 0.3688 1.0000
5.000 1.0525 0.01129 0.00500 -0.0852 0.3631 1.0000
5.250 1.0737 0.01138 0.00512 -0.0839 0.3569 1.0000
5.500 1.0938 0.01151 0.00525 -0.0824 0.3490 1.0000
5.750 1.1141 0.01164 0.00538 -0.0810 0.3412 1.0000
6.000 1.1336 0.01179 0.00552 -0.0794 0.3324 1.0000
6.250 1.1536 0.01193 0.00567 -0.0779 0.3228 1.0000
6.500 1.1718 0.01212 0.00584 -0.0760 0.3090 1.0000
6.750 1.1885 0.01238 0.00603 -0.0739 0.2907 1.0000
7.000 1.2025 0.01276 0.00629 -0.0714 0.2681 1.0000
7.250 1.2147 0.01321 0.00662 -0.0685 0.2445 1.0000
7.500 1.2260 0.01368 0.00699 -0.0655 0.2258 1.0000
8.000 1.2470 0.01446 0.00768 -0.0590 0.2027 1.0000
8.250 1.2581 0.01485 0.00804 -0.0560 0.1941 1.0000
8.500 1.2691 0.01527 0.00844 -0.0530 0.1858 1.0000
8.750 1.2820 0.01565 0.00883 -0.0504 0.1784 1.0000
9.000 1.2934 0.01612 0.00927 -0.0476 0.1709 1.0000
9.250 1.3073 0.01650 0.00967 -0.0453 0.1635 1.0000
9.500 1.3180 0.01705 0.01020 -0.0426 0.1548 1.0000
9.750 1.3310 0.01753 0.01065 -0.0403 0.1428 1.0000
10.000 1.3419 0.01813 0.01119 -0.0377 0.1252 1.0000
10.250 1.3354 0.01966 0.01239 -0.0328 0.0797 1.0000
10.500 1.3293 0.02126 0.01382 -0.0282 0.0466 1.0000
10.750 1.3312 0.02249 0.01501 -0.0249 0.0392 1.0000
11.000 1.3369 0.02357 0.01614 -0.0223 0.0360 1.0000
11.250 1.3443 0.02459 0.01725 -0.0200 0.0344 1.0000
11.500 1.3499 0.02578 0.01854 -0.0177 0.0330 1.0000
11.750 1.3531 0.02721 0.02007 -0.0153 0.0317 1.0000
12.000 1.3541 0.02890 0.02185 -0.0131 0.0306 1.0000
12.250 1.3511 0.03102 0.02407 -0.0108 0.0293 1.0000
12.500 1.3478 0.03328 0.02645 -0.0089 0.0285 1.0000
12.750 1.3521 0.03501 0.02828 -0.0076 0.0277 1.0000
13.000 1.3529 0.03711 0.03049 -0.0064 0.0269 1.0000
13.250 1.3518 0.03951 0.03298 -0.0053 0.0261 1.0000
13.500 1.3490 0.04218 0.03575 -0.0044 0.0253 1.0000
13.750 1.3425 0.04537 0.03904 -0.0036 0.0248 1.0000
14.000 1.3360 0.04871 0.04248 -0.0032 0.0242 1.0000
14.250 1.3245 0.05278 0.04665 -0.0031 0.0236 1.0000
14.500 1.3043 0.05808 0.05206 -0.0032 0.0230 1.0000
14.750 1.3001 0.06163 0.05572 -0.0035 0.0226 1.0000
15.000 1.2996 0.06483 0.05903 -0.0039 0.0221 1.0000
15.250 1.2939 0.06870 0.06300 -0.0045 0.0219 1.0000
15.500 1.2911 0.07233 0.06673 -0.0051 0.0213 1.0000
15.750 1.2852 0.07635 0.07084 -0.0058 0.0207 1.0000
16.000 1.2819 0.08009 0.07466 -0.0066 0.0202 1.0000
16.250 1.2770 0.08399 0.07863 -0.0074 0.0199 1.0000
16.500 1.2729 0.08783 0.08254 -0.0083 0.0194 1.0000
16.750 1.2677 0.09176 0.08653 -0.0091 0.0191 1.0000
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Polar data table (+)
Polar graphs
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