GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 561 AIRFOIL (goe561-il) Reynolds number: 500,000 Max Cl/Cd: 32.97 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe561-il-500000-n5.txt Download as CSV file: xf-goe561-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 561 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.5528 0.09900 0.09337 -0.1702 0.4997 0.0256
-11.750 0.5598 0.09707 0.09144 -0.1706 0.4981 0.0260
-11.500 0.5666 0.09518 0.08954 -0.1711 0.4962 0.0263
-11.250 0.5728 0.09326 0.08761 -0.1714 0.4944 0.0265
-11.000 0.5759 0.09101 0.08536 -0.1721 0.4930 0.0276
-10.750 0.5810 0.08897 0.08335 -0.1725 0.4922 0.0277
-10.500 0.5817 0.08664 0.08104 -0.1730 0.4909 0.0279
-10.250 0.5827 0.08443 0.07885 -0.1735 0.4899 0.0279
-10.000 0.5836 0.08213 0.07659 -0.1739 0.4887 0.0280
-9.750 0.5861 0.08004 0.07452 -0.1740 0.4876 0.0280
-9.500 0.5800 0.07720 0.07172 -0.1747 0.4866 0.0281
-9.250 0.5846 0.07524 0.06977 -0.1742 0.4854 0.0282
-9.000 0.5809 0.07282 0.06738 -0.1745 0.4842 0.0281
-8.750 0.5793 0.07057 0.06516 -0.1742 0.4827 0.0281
-8.250 0.5732 0.06627 0.06090 -0.1731 0.4795 0.0281
-8.000 0.5656 0.06395 0.05860 -0.1724 0.4779 0.0281
-7.750 0.5584 0.06189 0.05657 -0.1716 0.4766 0.0280
-7.500 0.5684 0.06175 0.05643 -0.1689 0.4743 0.0284
-7.250 0.5292 0.05777 0.05250 -0.1687 0.4737 0.0280
-7.000 0.4981 0.05560 0.05034 -0.1640 0.4727 0.0280
-6.750 0.4766 0.05458 0.04937 -0.1582 0.4716 0.0280
-6.500 0.4588 0.05392 0.04876 -0.1522 0.4706 0.0279
-6.250 0.4612 0.05379 0.04868 -0.1487 0.4692 0.0274
-6.000 0.4377 0.05214 0.04705 -0.1425 0.4677 0.0274
-5.750 0.4223 0.05076 0.04568 -0.1372 0.4663 0.0267
-5.500 0.4043 0.04893 0.04382 -0.1316 0.4654 0.0264
-5.250 0.3890 0.04724 0.04209 -0.1260 0.4641 0.0264
-5.000 0.3722 0.04517 0.03995 -0.1199 0.4627 0.0260
-4.750 0.3445 0.04181 0.03643 -0.1118 0.4616 0.0252
-4.500 0.3500 0.04153 0.03615 -0.1087 0.4600 0.0257
-4.250 0.3344 0.03905 0.03351 -0.1019 0.4585 0.0254
-4.000 0.3231 0.03695 0.03126 -0.0954 0.4572 0.0252
-3.750 0.3242 0.03608 0.03031 -0.0912 0.4555 0.0254
-3.500 0.3212 0.03470 0.02879 -0.0860 0.4537 0.0255
-3.250 0.3250 0.03381 0.02784 -0.0820 0.4528 0.0257
-3.000 0.3255 0.03257 0.02651 -0.0772 0.4514 0.0259
-2.750 0.3222 0.03092 0.02469 -0.0714 0.4502 0.0257
-2.500 0.3213 0.02959 0.02320 -0.0661 0.4482 0.0257
-2.250 0.3200 0.02813 0.02154 -0.0605 0.4465 0.0256
-2.000 0.3229 0.02705 0.02029 -0.0557 0.4449 0.0257
-1.750 0.3261 0.02605 0.01911 -0.0510 0.4429 0.0258
-1.500 0.3328 0.02526 0.01817 -0.0470 0.4413 0.0261
-1.250 0.3395 0.02444 0.01717 -0.0430 0.4394 0.0263
-1.000 0.3478 0.02368 0.01620 -0.0392 0.4375 0.0268
-0.750 0.3598 0.02287 0.01520 -0.0362 0.4358 0.0268
-0.500 0.3774 0.02193 0.01406 -0.0342 0.4342 0.0272
-0.250 0.3987 0.02118 0.01314 -0.0331 0.4322 0.0275
0.000 0.4233 0.02061 0.01238 -0.0327 0.4302 0.0279
0.250 0.4404 0.02061 0.01237 -0.0312 0.4276 0.0284
0.500 0.4593 0.02054 0.01226 -0.0301 0.4247 0.0286
0.750 0.4779 0.02058 0.01226 -0.0289 0.4226 0.0288
1.000 0.4952 0.02068 0.01231 -0.0276 0.4201 0.0291
1.250 0.5184 0.02064 0.01223 -0.0274 0.4178 0.0294
1.500 0.5419 0.02066 0.01225 -0.0273 0.4157 0.0298
1.750 0.5648 0.02072 0.01229 -0.0271 0.4126 0.0304
2.000 0.5896 0.02077 0.01231 -0.0274 0.4101 0.0308
2.250 0.6115 0.02094 0.01244 -0.0273 0.4064 0.0311
2.500 0.6305 0.02125 0.01269 -0.0267 0.4033 0.0316
2.750 0.6562 0.02141 0.01286 -0.0274 0.4010 0.0318
3.000 0.6789 0.02168 0.01317 -0.0275 0.3981 0.0325
3.250 0.7012 0.02202 0.01352 -0.0277 0.3947 0.0330
3.500 0.7221 0.02245 0.01396 -0.0278 0.3913 0.0337
3.750 0.7430 0.02298 0.01445 -0.0281 0.3880 0.0349
4.000 0.7669 0.02345 0.01492 -0.0288 0.3848 0.0355
4.250 0.7896 0.02395 0.01545 -0.0294 0.3807 0.0364
4.500 0.8078 0.02459 0.01611 -0.0294 0.3768 0.0373
4.750 0.8237 0.02533 0.01683 -0.0290 0.3734 0.0382
5.000 0.8403 0.02606 0.01754 -0.0288 0.3703 0.0390
5.250 0.8586 0.02672 0.01824 -0.0287 0.3671 0.0404
5.500 0.8747 0.02748 0.01901 -0.0284 0.3637 0.0414
5.750 0.8868 0.02845 0.01998 -0.0276 0.3602 0.0428
6.000 0.8978 0.02950 0.02101 -0.0269 0.3567 0.0446
6.250 0.9124 0.03036 0.02191 -0.0264 0.3539 0.0470
6.500 0.9261 0.03132 0.02288 -0.0260 0.3507 0.0496
6.750 0.9383 0.03233 0.02391 -0.0254 0.3474 0.0514
7.000 0.9472 0.03360 0.02518 -0.0246 0.3442 0.0550
7.250 0.9547 0.03495 0.02652 -0.0237 0.3403 0.0603
7.500 0.9686 0.03600 0.02767 -0.0235 0.3376 0.0901
8.000 1.2556 0.04059 0.03428 -0.0778 0.3288 1.0000
8.250 1.2593 0.04233 0.03601 -0.0766 0.3264 1.0000
8.500 1.2653 0.04396 0.03765 -0.0756 0.3228 1.0000
8.750 1.2706 0.04565 0.03936 -0.0746 0.3200 1.0000
9.000 1.2755 0.04740 0.04112 -0.0737 0.3174 1.0000
9.250 1.2786 0.04932 0.04304 -0.0726 0.3145 1.0000
9.500 1.2806 0.05135 0.04506 -0.0716 0.3120 1.0000
9.750 1.2850 0.05323 0.04695 -0.0708 0.3092 1.0000
10.000 1.2905 0.05506 0.04881 -0.0701 0.3072 1.0000
10.250 1.2983 0.05666 0.05043 -0.0696 0.3056 1.0000
10.500 1.3019 0.05866 0.05246 -0.0688 0.3034 1.0000
10.750 1.3048 0.06074 0.05455 -0.0681 0.3008 1.0000
11.000 1.3105 0.06255 0.05635 -0.0676 0.2990 1.0000
11.250 1.3126 0.06471 0.05850 -0.0668 0.2967 1.0000
11.500 1.3171 0.06671 0.06053 -0.0663 0.2943 1.0000
11.750 1.3258 0.06828 0.06213 -0.0660 0.2933 1.0000
12.000 1.3292 0.07043 0.06433 -0.0656 0.2914 1.0000
12.250 1.3336 0.07243 0.06636 -0.0651 0.2893 1.0000
12.500 1.3359 0.07466 0.06859 -0.0647 0.2862 1.0000
12.750 1.3372 0.07700 0.07093 -0.0642 0.2837 1.0000
13.000 1.3402 0.07915 0.07307 -0.0637 0.2809 1.0000
13.250 1.3503 0.08058 0.07453 -0.0636 0.2804 1.0000
13.500 1.3553 0.08260 0.07660 -0.0634 0.2787 1.0000
13.750 1.3573 0.08493 0.07898 -0.0631 0.2768 1.0000
14.000 1.3610 0.08708 0.08116 -0.0629 0.2747 1.0000
14.250 1.3662 0.08903 0.08314 -0.0627 0.2728 1.0000
14.500 1.3730 0.09083 0.08495 -0.0626 0.2713 1.0000
14.750 1.3777 0.09284 0.08696 -0.0625 0.2695 1.0000
15.000 1.3844 0.09462 0.08873 -0.0624 0.2679 1.0000
15.250 1.3932 0.09615 0.09029 -0.0625 0.2669 1.0000
15.500 1.3964 0.09839 0.09260 -0.0624 0.2655 1.0000
15.750 1.3991 0.10066 0.09493 -0.0623 0.2638 1.0000
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