GOE 776 AIRFOIL (goe776-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 776 AIRFOIL (goe776-il) Reynolds number: 100,000 Max Cl/Cd: 28.8 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe776-il-100000-n5.txt Download as CSV file: xf-goe776-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 776 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8674 0.09284 0.08468 -0.0523 1.0000 0.1569
-16.500 -0.9122 0.08366 0.07526 -0.0554 1.0000 0.1611
-16.250 -0.8962 0.08289 0.07455 -0.0553 1.0000 0.1637
-16.000 -0.9084 0.07843 0.07001 -0.0564 1.0000 0.1672
-15.750 -0.9457 0.07101 0.06230 -0.0583 1.0000 0.1713
-15.500 -0.9385 0.06922 0.06054 -0.0583 1.0000 0.1742
-15.250 -0.9322 0.06736 0.05871 -0.0583 1.0000 0.1773
-15.000 -0.9402 0.06392 0.05517 -0.0586 1.0000 0.1810
-14.750 -0.9599 0.05936 0.05040 -0.0589 1.0000 0.1849
-14.500 -0.9475 0.05832 0.04944 -0.0585 1.0000 0.1879
-14.250 -0.9437 0.05645 0.04758 -0.0581 1.0000 0.1914
-14.000 -0.9489 0.05378 0.04482 -0.0576 1.0000 0.1954
-13.750 -0.9578 0.05091 0.04180 -0.0568 1.0000 0.1994
-13.500 -0.9473 0.04990 0.04089 -0.0560 1.0000 0.2027
-13.250 -0.9451 0.04827 0.03924 -0.0550 1.0000 0.2065
-13.000 -0.9494 0.04622 0.03711 -0.0536 1.0000 0.2108
-12.750 -0.9514 0.04449 0.03532 -0.0519 1.0000 0.2147
-12.500 -0.9455 0.04348 0.03438 -0.0503 1.0000 0.2183
-12.250 -0.9460 0.04216 0.03305 -0.0483 1.0000 0.2223
-12.000 -0.9514 0.04067 0.03148 -0.0457 1.0000 0.2268
-11.750 -0.9525 0.03955 0.03036 -0.0431 1.0000 0.2307
-11.500 -0.9513 0.03872 0.02959 -0.0404 1.0000 0.2344
-11.250 -0.9554 0.03777 0.02863 -0.0372 1.0000 0.2385
-11.000 -0.9635 0.03677 0.02757 -0.0333 1.0000 0.2429
-10.750 -0.9689 0.03602 0.02682 -0.0294 1.0000 0.2467
-10.500 -0.9735 0.03544 0.02631 -0.0253 1.0000 0.2503
-10.250 -0.9826 0.03483 0.02569 -0.0207 1.0000 0.2543
-10.000 -0.9703 0.03389 0.02465 -0.0200 0.9958 0.2603
-9.750 -0.9424 0.03315 0.02396 -0.0217 0.9906 0.2661
-9.500 -0.9187 0.03233 0.02313 -0.0225 0.9831 0.2727
-9.250 -0.8928 0.03150 0.02220 -0.0238 0.9768 0.2798
-9.000 -0.8676 0.03090 0.02168 -0.0245 0.9690 0.2857
-8.750 -0.8413 0.03019 0.02091 -0.0255 0.9619 0.2932
-8.500 -0.8160 0.02956 0.02028 -0.0261 0.9541 0.2999
-8.250 -0.7896 0.02900 0.01975 -0.0267 0.9460 0.3067
-8.000 -0.7610 0.02829 0.01893 -0.0279 0.9399 0.3151
-7.750 -0.7404 0.02788 0.01862 -0.0270 0.9286 0.3210
-7.500 -0.7115 0.02729 0.01800 -0.0278 0.9218 0.3290
-7.250 -0.6968 0.02684 0.01752 -0.0259 0.9092 0.3359
-7.000 -0.6668 0.02635 0.01709 -0.0266 0.9019 0.3432
-6.750 -0.6511 0.02595 0.01663 -0.0247 0.8895 0.3508
-6.500 -0.6230 0.02547 0.01618 -0.0249 0.8811 0.3581
-6.250 -0.6028 0.02513 0.01585 -0.0236 0.8699 0.3654
-6.000 -0.5817 0.02467 0.01528 -0.0225 0.8595 0.3738
-5.750 -0.5554 0.02434 0.01505 -0.0222 0.8497 0.3806
-5.500 -0.5345 0.02400 0.01468 -0.0210 0.8382 0.3885
-5.250 -0.5097 0.02361 0.01424 -0.0204 0.8289 0.3965
-5.000 -0.4882 0.02337 0.01406 -0.0191 0.8165 0.4037
-4.750 -0.4621 0.02298 0.01358 -0.0187 0.8080 0.4126
-4.500 -0.4425 0.02278 0.01343 -0.0172 0.7947 0.4197
-4.250 -0.4146 0.02245 0.01309 -0.0170 0.7857 0.4281
-4.000 -0.3979 0.02227 0.01282 -0.0150 0.7726 0.4368
-3.750 -0.3684 0.02199 0.01261 -0.0150 0.7630 0.4443
-3.500 -0.3484 0.02184 0.01244 -0.0135 0.7506 0.4530
-3.250 -0.3230 0.02159 0.01216 -0.0129 0.7403 0.4616
-3.000 -0.2999 0.02146 0.01207 -0.0119 0.7285 0.4698
-2.750 -0.2773 0.02126 0.01177 -0.0107 0.7176 0.4796
-2.500 -0.2520 0.02114 0.01172 -0.0101 0.7065 0.4876
-2.250 -0.2289 0.02101 0.01155 -0.0090 0.6952 0.4971
-2.000 -0.2047 0.02088 0.01140 -0.0082 0.6845 0.5063
-1.750 -0.1811 0.02080 0.01135 -0.0072 0.6730 0.5154
-1.500 -0.1574 0.02067 0.01113 -0.0063 0.6631 0.5258
-1.250 -0.1335 0.02064 0.01119 -0.0054 0.6510 0.5345
-1.000 -0.1084 0.02053 0.01097 -0.0047 0.6418 0.5454
-0.750 -0.0860 0.02053 0.01106 -0.0035 0.6297 0.5543
-0.500 -0.0608 0.02047 0.01094 -0.0028 0.6198 0.5650
-0.250 -0.0386 0.02046 0.01096 -0.0016 0.6087 0.5748
0.000 -0.0134 0.02045 0.01094 -0.0009 0.5985 0.5850
0.250 0.0088 0.02043 0.01090 0.0002 0.5882 0.5960
0.500 0.0340 0.02046 0.01098 0.0010 0.5775 0.6057
0.750 0.0567 0.02045 0.01087 0.0021 0.5683 0.6175
1.000 0.0815 0.02052 0.01106 0.0028 0.5572 0.6268
1.250 0.1060 0.02053 0.01097 0.0037 0.5484 0.6386
1.500 0.1291 0.02062 0.01116 0.0047 0.5376 0.6484
1.750 0.1532 0.02067 0.01118 0.0056 0.5283 0.6599
2.000 0.1768 0.02077 0.01130 0.0065 0.5186 0.6705
2.250 0.2006 0.02087 0.01142 0.0074 0.5090 0.6815
2.500 0.2248 0.02095 0.01146 0.0083 0.5004 0.6929
2.750 0.2482 0.02112 0.01171 0.0093 0.4904 0.7037
3.000 0.2717 0.02120 0.01172 0.0102 0.4823 0.7155
3.250 0.2964 0.02142 0.01202 0.0110 0.4729 0.7258
3.500 0.3171 0.02153 0.01211 0.0124 0.4643 0.7385
3.750 0.3453 0.02178 0.01236 0.0126 0.4562 0.7481
4.000 0.3630 0.02192 0.01254 0.0145 0.4473 0.7613
4.250 0.3924 0.02220 0.01280 0.0144 0.4392 0.7705
4.500 0.4115 0.02240 0.01302 0.0161 0.4312 0.7834
4.750 0.4377 0.02271 0.01338 0.0165 0.4224 0.7927
5.000 0.4616 0.02294 0.01351 0.0174 0.4155 0.8049
5.250 0.4839 0.02328 0.01397 0.0184 0.4067 0.8147
5.500 0.5065 0.02357 0.01423 0.0195 0.3990 0.8263
5.750 0.5308 0.02389 0.01454 0.0202 0.3917 0.8366
6.000 0.5529 0.02428 0.01499 0.0212 0.3833 0.8472
6.250 0.5752 0.02457 0.01523 0.0222 0.3763 0.8584
6.500 0.6005 0.02503 0.01573 0.0225 0.3684 0.8677
6.750 0.6179 0.02537 0.01609 0.0243 0.3609 0.8800
7.000 0.6494 0.02582 0.01644 0.0236 0.3538 0.8876
7.250 0.6626 0.02622 0.01695 0.0259 0.3463 0.9008
7.500 0.6921 0.02674 0.01746 0.0253 0.3385 0.9079
7.750 0.7083 0.02712 0.01780 0.0271 0.3323 0.9208
8.000 0.7371 0.02775 0.01850 0.0262 0.3239 0.9273
8.250 0.7597 0.02820 0.01889 0.0267 0.3174 0.9376
8.500 0.7864 0.02883 0.01956 0.0260 0.3098 0.9450
8.750 0.8132 0.02943 0.02018 0.0252 0.3024 0.9527
9.000 0.8391 0.02997 0.02063 0.0247 0.2963 0.9610
9.250 0.8654 0.03072 0.02150 0.0236 0.2885 0.9678
9.500 0.8886 0.03136 0.02210 0.0232 0.2822 0.9763
9.750 0.9172 0.03209 0.02285 0.0216 0.2756 0.9820
10.000 0.9404 0.03294 0.02376 0.0208 0.2687 0.9897
10.250 0.9684 0.03363 0.02438 0.0192 0.2628 0.9950
10.500 0.9858 0.03459 0.02543 0.0190 0.2567 1.0000
10.750 0.9757 0.03521 0.02608 0.0238 0.2526 1.0000
11.000 0.9692 0.03583 0.02666 0.0281 0.2487 1.0000
11.250 0.9681 0.03639 0.02712 0.0316 0.2452 1.0000
11.500 0.9584 0.03741 0.02824 0.0357 0.2409 1.0000
11.750 0.9530 0.03841 0.02927 0.0392 0.2366 1.0000
12.000 0.9520 0.03933 0.03017 0.0420 0.2326 1.0000
12.250 0.9566 0.04011 0.03085 0.0443 0.2290 1.0000
12.500 0.9493 0.04168 0.03254 0.0471 0.2246 1.0000
12.750 0.9470 0.04309 0.03399 0.0493 0.2203 1.0000
13.000 0.9501 0.04428 0.03515 0.0510 0.2165 1.0000
13.250 0.9553 0.04547 0.03629 0.0524 0.2128 1.0000
13.500 0.9488 0.04766 0.03861 0.0539 0.2085 1.0000
13.750 0.9485 0.04950 0.04049 0.0550 0.2045 1.0000
14.000 0.9552 0.05082 0.04176 0.0559 0.2009 1.0000
14.250 0.9561 0.05280 0.04377 0.0566 0.1973 1.0000
14.500 0.9479 0.05573 0.04684 0.0571 0.1932 1.0000
14.750 0.9484 0.05793 0.04906 0.0575 0.1895 1.0000
15.000 0.9589 0.05916 0.05022 0.0579 0.1863 1.0000
15.250 0.9494 0.06259 0.05378 0.0578 0.1827 1.0000
15.500 0.9369 0.06652 0.05785 0.0575 0.1789 1.0000
15.750 0.9385 0.06894 0.06028 0.0573 0.1755 1.0000
16.000 0.9543 0.06971 0.06095 0.0576 0.1728 1.0000
16.250 0.9229 0.07630 0.06780 0.0560 0.1689 1.0000
16.500 0.9009 0.08202 0.07367 0.0545 0.1650 1.0000
16.750 0.9100 0.08371 0.07533 0.0543 0.1621 1.0000
17.000 0.9313 0.08379 0.07530 0.0546 0.1599 1.0000
17.250 0.7957 0.10640 0.09852 0.0462 0.1514 1.0000
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