GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 200,000 Max Cl/Cd: 54.61 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe513-il-200000-n5.txt Download as CSV file: xf-goe513-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2530 0.09600 0.09206 -0.0778 0.9735 0.0355
-11.500 -0.4520 0.05354 0.04901 -0.1106 0.9623 0.0347
-11.250 -0.4794 0.04803 0.04312 -0.1122 0.9561 0.0348
-11.000 -0.5027 0.04536 0.04020 -0.1080 0.9467 0.0349
-10.750 -0.5130 0.04262 0.03712 -0.1051 0.9409 0.0351
-10.500 -0.5268 0.04076 0.03502 -0.0997 0.9307 0.0353
-10.250 -0.5230 0.03822 0.03211 -0.0976 0.9257 0.0355
-10.000 -0.5280 0.03668 0.03032 -0.0926 0.9157 0.0357
-9.750 -0.5164 0.03486 0.02817 -0.0908 0.9107 0.0359
-9.500 -0.5073 0.03341 0.02661 -0.0880 0.9038 0.0361
-9.250 -0.4943 0.03217 0.02527 -0.0857 0.8969 0.0363
-9.000 -0.4719 0.03079 0.02375 -0.0853 0.8937 0.0366
-8.750 -0.4650 0.02991 0.02277 -0.0815 0.8840 0.0368
-8.500 -0.4438 0.02877 0.02151 -0.0804 0.8792 0.0373
-8.250 -0.4233 0.02775 0.02037 -0.0792 0.8740 0.0378
-8.000 -0.4111 0.02699 0.01950 -0.0762 0.8650 0.0383
-7.750 -0.3849 0.02592 0.01829 -0.0760 0.8614 0.0389
-7.500 -0.3711 0.02519 0.01743 -0.0732 0.8518 0.0393
-7.250 -0.3439 0.02418 0.01626 -0.0730 0.8462 0.0399
-7.000 -0.3196 0.02332 0.01528 -0.0722 0.8393 0.0403
-6.750 -0.2941 0.02253 0.01436 -0.0715 0.8317 0.0407
-6.500 -0.2572 0.02157 0.01331 -0.0732 0.8271 0.0412
-6.250 -0.2354 0.02086 0.01260 -0.0720 0.8178 0.0417
-6.000 -0.1985 0.02004 0.01176 -0.0738 0.8116 0.0423
-5.750 -0.1691 0.01942 0.01110 -0.0740 0.8028 0.0431
-5.500 -0.1311 0.01879 0.01041 -0.0760 0.7949 0.0444
-5.250 -0.0972 0.01825 0.00980 -0.0771 0.7857 0.0455
-5.000 -0.0596 0.01772 0.00916 -0.0790 0.7756 0.0466
-4.750 -0.0329 0.01724 0.00865 -0.0787 0.7641 0.0475
-4.500 -0.0006 0.01680 0.00815 -0.0795 0.7534 0.0487
-4.250 0.0248 0.01649 0.00777 -0.0789 0.7408 0.0499
-4.000 0.0504 0.01624 0.00743 -0.0783 0.7281 0.0512
-3.750 0.0778 0.01602 0.00707 -0.0780 0.7150 0.0530
-3.500 0.0995 0.01577 0.00678 -0.0766 0.7007 0.0555
-3.250 0.1206 0.01559 0.00652 -0.0750 0.6855 0.0587
-3.000 0.1411 0.01539 0.00627 -0.0733 0.6685 0.0631
-2.750 0.1604 0.01519 0.00603 -0.0714 0.6487 0.0703
-2.500 0.1790 0.01476 0.00573 -0.0695 0.6260 0.1107
-2.250 0.1946 0.01456 0.00576 -0.0670 0.6026 0.1874
-2.000 0.2097 0.01468 0.00577 -0.0642 0.5815 0.2125
-1.750 0.2245 0.01483 0.00580 -0.0613 0.5655 0.2283
-1.500 0.2399 0.01497 0.00582 -0.0586 0.5528 0.2393
-1.250 0.2570 0.01510 0.00584 -0.0562 0.5416 0.2483
-1.000 0.2749 0.01523 0.00584 -0.0541 0.5311 0.2551
-0.750 0.2925 0.01534 0.00588 -0.0519 0.5204 0.2620
-0.500 0.3110 0.01551 0.00592 -0.0499 0.5109 0.2715
-0.250 0.3288 0.01560 0.00600 -0.0478 0.5019 0.2806
0.000 0.3493 0.01574 0.00602 -0.0462 0.4947 0.2881
0.250 0.3697 0.01574 0.00603 -0.0446 0.4881 0.2921
0.500 0.3902 0.01578 0.00603 -0.0431 0.4816 0.2954
0.750 0.4108 0.01585 0.00605 -0.0416 0.4754 0.2991
1.000 0.4308 0.01588 0.00607 -0.0400 0.4695 0.3031
1.250 0.4509 0.01595 0.00610 -0.0384 0.4637 0.3070
1.500 0.4706 0.01601 0.00613 -0.0367 0.4584 0.3113
1.750 0.4897 0.01603 0.00619 -0.0350 0.4530 0.3165
2.000 0.5082 0.01609 0.00625 -0.0331 0.4471 0.3223
2.250 0.5257 0.01617 0.00631 -0.0310 0.4411 0.3280
2.500 0.5429 0.01622 0.00638 -0.0289 0.4355 0.3343
2.750 0.5598 0.01628 0.00646 -0.0267 0.4290 0.3413
3.000 0.5754 0.01636 0.00653 -0.0243 0.4227 0.3492
3.250 0.5919 0.01644 0.00663 -0.0221 0.4168 0.3601
3.500 0.6084 0.01649 0.00673 -0.0199 0.4103 0.3734
3.750 0.6237 0.01655 0.00684 -0.0176 0.4042 0.3963
4.250 0.8614 0.01721 0.00887 -0.0568 0.3760 0.9700
4.750 0.9280 0.01794 0.00948 -0.0599 0.3575 0.9851
5.000 0.9662 0.01834 0.00981 -0.0626 0.3484 0.9920
5.250 1.0051 0.01864 0.01006 -0.0655 0.3388 0.9969
5.500 1.0360 0.01897 0.01033 -0.0667 0.3307 1.0000
5.750 1.0470 0.01924 0.01059 -0.0638 0.3238 1.0000
6.000 1.0560 0.01959 0.01088 -0.0606 0.3176 1.0000
6.250 1.0679 0.01990 0.01119 -0.0579 0.3116 1.0000
6.500 1.0786 0.02026 0.01152 -0.0550 0.3054 1.0000
7.000 1.1006 0.02104 0.01225 -0.0495 0.2945 1.0000
7.250 1.1114 0.02147 0.01266 -0.0468 0.2887 1.0000
7.500 1.1215 0.02195 0.01309 -0.0441 0.2842 1.0000
7.750 1.1339 0.02239 0.01353 -0.0417 0.2800 1.0000
8.000 1.1465 0.02283 0.01399 -0.0395 0.2757 1.0000
8.250 1.1582 0.02333 0.01449 -0.0371 0.2718 1.0000
8.500 1.1688 0.02390 0.01502 -0.0347 0.2683 1.0000
8.750 1.1807 0.02444 0.01555 -0.0325 0.2653 1.0000
9.000 1.1943 0.02494 0.01610 -0.0306 0.2620 1.0000
9.250 1.2066 0.02549 0.01668 -0.0286 0.2586 1.0000
9.500 1.2180 0.02610 0.01730 -0.0265 0.2552 1.0000
9.750 1.2291 0.02675 0.01794 -0.0244 0.2525 1.0000
10.000 1.2403 0.02745 0.01861 -0.0224 0.2500 1.0000
10.250 1.2534 0.02806 0.01928 -0.0207 0.2477 1.0000
10.500 1.2666 0.02869 0.01997 -0.0191 0.2456 1.0000
10.750 1.2790 0.02937 0.02070 -0.0174 0.2432 1.0000
11.000 1.2907 0.03010 0.02147 -0.0157 0.2408 1.0000
11.250 1.3020 0.03086 0.02227 -0.0141 0.2385 1.0000
11.500 1.3130 0.03166 0.02308 -0.0124 0.2363 1.0000
11.750 1.3244 0.03249 0.02389 -0.0109 0.2340 1.0000
12.000 1.3371 0.03327 0.02470 -0.0095 0.2322 1.0000
12.250 1.3483 0.03412 0.02566 -0.0081 0.2305 1.0000
12.500 1.3594 0.03501 0.02664 -0.0067 0.2288 1.0000
12.750 1.3694 0.03597 0.02769 -0.0052 0.2267 1.0000
13.000 1.3786 0.03699 0.02878 -0.0038 0.2245 1.0000
13.250 1.3878 0.03804 0.02989 -0.0025 0.2226 1.0000
13.500 1.3977 0.03908 0.03097 -0.0012 0.2207 1.0000
13.750 1.4085 0.04007 0.03198 -0.0001 0.2191 1.0000
14.000 1.4214 0.04098 0.03289 0.0009 0.2174 1.0000
14.250 1.4291 0.04222 0.03423 0.0021 0.2156 1.0000
14.500 1.4324 0.04379 0.03596 0.0035 0.2134 1.0000
14.750 1.4374 0.04530 0.03758 0.0046 0.2114 1.0000
15.000 1.4397 0.04703 0.03941 0.0058 0.2086 1.0000
15.250 1.4428 0.04873 0.04119 0.0068 0.2060 1.0000
15.500 1.4484 0.05025 0.04273 0.0077 0.2035 1.0000
15.750 1.4558 0.05163 0.04408 0.0085 0.2007 1.0000
16.000 1.4548 0.05389 0.04652 0.0094 0.1989 1.0000
16.250 1.4514 0.05647 0.04927 0.0101 0.1963 1.0000
16.500 1.4520 0.05872 0.05164 0.0106 0.1944 1.0000
16.750 1.4486 0.06142 0.05445 0.0110 0.1913 1.0000
17.000 1.4497 0.06368 0.05676 0.0113 0.1888 1.0000
17.250 1.4550 0.06546 0.05855 0.0116 0.1867 1.0000
17.500 1.4517 0.06837 0.06159 0.0117 0.1846 1.0000
17.750 1.4425 0.07210 0.06552 0.0115 0.1823 1.0000
18.000 1.4326 0.07602 0.06960 0.0111 0.1795 1.0000
18.250 1.4259 0.07955 0.07324 0.0107 0.1772 1.0000
18.500 1.4215 0.08279 0.07654 0.0103 0.1742 1.0000
18.750 1.4220 0.08537 0.07914 0.0100 0.1714 1.0000
19.000 1.4038 0.09065 0.08463 0.0090 0.1692 1.0000
19.250 1.3818 0.09654 0.09072 0.0076 0.1664 1.0000
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Polar data table (+)
Polar graphs
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