GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.26 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe633-il-1000000.txt Download as CSV file: xf-goe633-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7857 0.05196 0.04952 -0.0654 1.0000 0.0251
-13.000 -0.8244 0.04126 0.03850 -0.0778 1.0000 0.0249
-12.750 -0.8439 0.03802 0.03508 -0.0767 1.0000 0.0250
-12.500 -0.8205 0.03476 0.03151 -0.0823 0.9354 0.0253
-12.250 -0.8201 0.03332 0.02953 -0.0800 0.8271 0.0254
-12.000 -0.8219 0.03210 0.02807 -0.0764 0.8050 0.0255
-11.750 -0.8166 0.03108 0.02685 -0.0737 0.7912 0.0256
-11.500 -0.8096 0.02995 0.02552 -0.0712 0.7800 0.0257
-11.250 -0.8046 0.02827 0.02361 -0.0685 0.7709 0.0258
-11.000 -0.8001 0.02578 0.02089 -0.0660 0.7625 0.0260
-10.750 -0.7869 0.02424 0.01922 -0.0641 0.7553 0.0262
-10.500 -0.7700 0.02318 0.01807 -0.0627 0.7484 0.0264
-10.250 -0.7518 0.02235 0.01714 -0.0612 0.7418 0.0266
-10.000 -0.7321 0.02157 0.01628 -0.0600 0.7361 0.0268
-9.750 -0.7118 0.02086 0.01548 -0.0588 0.7297 0.0270
-9.500 -0.6909 0.02026 0.01478 -0.0576 0.7235 0.0273
-9.250 -0.6684 0.01971 0.01420 -0.0567 0.7185 0.0276
-9.000 -0.6465 0.01907 0.01348 -0.0556 0.7130 0.0279
-8.750 -0.6244 0.01843 0.01273 -0.0546 0.7076 0.0281
-8.500 -0.6018 0.01779 0.01201 -0.0536 0.7027 0.0283
-8.250 -0.5786 0.01716 0.01131 -0.0527 0.6975 0.0285
-8.000 -0.5553 0.01659 0.01065 -0.0517 0.6921 0.0287
-7.750 -0.5315 0.01609 0.01007 -0.0509 0.6868 0.0290
-7.500 -0.5071 0.01557 0.00949 -0.0501 0.6824 0.0292
-7.250 -0.4824 0.01513 0.00899 -0.0493 0.6774 0.0294
-7.000 -0.4575 0.01475 0.00853 -0.0486 0.6724 0.0296
-6.750 -0.4322 0.01440 0.00812 -0.0479 0.6675 0.0298
-6.500 -0.4072 0.01392 0.00760 -0.0472 0.6626 0.0300
-6.250 -0.3850 0.01308 0.00672 -0.0461 0.6576 0.0305
-6.000 -0.3606 0.01264 0.00623 -0.0453 0.6523 0.0309
-5.750 -0.3349 0.01228 0.00586 -0.0447 0.6470 0.0314
-5.500 -0.3091 0.01197 0.00552 -0.0441 0.6407 0.0318
-5.250 -0.2833 0.01170 0.00519 -0.0434 0.6345 0.0322
-5.000 -0.2569 0.01141 0.00488 -0.0429 0.6293 0.0326
-4.750 -0.2305 0.01115 0.00458 -0.0424 0.6227 0.0330
-4.500 -0.2043 0.01094 0.00431 -0.0418 0.6162 0.0334
-4.250 -0.1773 0.01070 0.00405 -0.0414 0.6110 0.0338
-4.000 -0.1502 0.01050 0.00383 -0.0410 0.6058 0.0342
-3.750 -0.1235 0.01030 0.00357 -0.0405 0.6005 0.0347
-3.500 -0.0971 0.01000 0.00323 -0.0400 0.5956 0.0356
-3.250 -0.0700 0.00978 0.00301 -0.0396 0.5901 0.0365
-3.000 -0.0428 0.00963 0.00283 -0.0392 0.5847 0.0375
-2.750 -0.0156 0.00951 0.00268 -0.0389 0.5796 0.0387
-2.500 0.0122 0.00938 0.00254 -0.0386 0.5749 0.0397
-2.250 0.0393 0.00919 0.00234 -0.0382 0.5695 0.0420
-2.000 0.0663 0.00909 0.00221 -0.0378 0.5636 0.0448
-1.750 0.0933 0.00884 0.00203 -0.0373 0.5587 0.0593
-1.500 0.1184 0.00844 0.00189 -0.0367 0.5531 0.1206
-1.250 0.1445 0.00827 0.00183 -0.0362 0.5475 0.1534
-1.000 0.1717 0.00817 0.00182 -0.0359 0.5426 0.1799
-0.750 0.1993 0.00813 0.00181 -0.0356 0.5369 0.1938
-0.500 0.2267 0.00813 0.00179 -0.0353 0.5310 0.2037
-0.250 0.2543 0.00810 0.00179 -0.0351 0.5253 0.2124
0.000 0.2822 0.00810 0.00178 -0.0348 0.5187 0.2185
0.500 0.3369 0.00808 0.00176 -0.0343 0.5054 0.2324
0.750 0.3640 0.00810 0.00176 -0.0339 0.4971 0.2391
1.000 0.3912 0.00809 0.00177 -0.0336 0.4888 0.2475
1.250 0.4183 0.00813 0.00178 -0.0333 0.4796 0.2547
1.500 0.4452 0.00811 0.00180 -0.0329 0.4714 0.2666
1.750 0.4716 0.00816 0.00182 -0.0325 0.4605 0.2764
2.000 0.4984 0.00817 0.00184 -0.0321 0.4488 0.2888
2.250 0.5242 0.00820 0.00188 -0.0316 0.4354 0.3086
2.500 0.5494 0.00820 0.00194 -0.0310 0.4225 0.3410
2.750 0.5719 0.00808 0.00201 -0.0300 0.4089 0.4292
3.000 0.5745 0.00684 0.00217 -0.0245 0.3978 0.9145
3.250 0.6111 0.00709 0.00238 -0.0262 0.3821 0.9470
3.500 0.6484 0.00738 0.00260 -0.0281 0.3675 0.9606
3.750 0.6863 0.00769 0.00284 -0.0300 0.3547 0.9694
4.000 0.7351 0.00804 0.00309 -0.0344 0.3428 0.9726
4.250 0.7744 0.00825 0.00327 -0.0368 0.3354 0.9759
4.500 0.8018 0.00851 0.00347 -0.0366 0.3283 0.9806
4.750 0.8429 0.00867 0.00361 -0.0394 0.3220 0.9823
5.000 0.8829 0.00887 0.00376 -0.0421 0.3145 0.9837
5.250 0.9198 0.00904 0.00389 -0.0440 0.3090 0.9853
5.500 0.9560 0.00918 0.00402 -0.0458 0.3036 0.9871
5.750 0.9884 0.00936 0.00417 -0.0468 0.2982 0.9889
6.000 1.0196 0.00954 0.00433 -0.0476 0.2934 0.9909
6.250 1.0487 0.00967 0.00447 -0.0479 0.2897 0.9927
6.500 1.0833 0.00980 0.00459 -0.0495 0.2849 0.9938
6.750 1.1184 0.00999 0.00475 -0.0512 0.2791 0.9951
7.000 1.1559 0.01009 0.00486 -0.0534 0.2749 0.9969
7.250 1.1952 0.01022 0.00498 -0.0559 0.2692 0.9990
7.500 1.2263 0.01043 0.00516 -0.0568 0.2628 1.0000
7.750 1.2488 0.01056 0.00531 -0.0559 0.2582 1.0000
8.000 1.2702 0.01075 0.00549 -0.0547 0.2515 1.0000
8.250 1.2907 0.01098 0.00570 -0.0535 0.2446 1.0000
8.500 1.3111 0.01120 0.00591 -0.0522 0.2359 1.0000
8.750 1.3295 0.01150 0.00616 -0.0506 0.2233 1.0000
9.000 1.3453 0.01193 0.00650 -0.0486 0.2058 1.0000
9.250 1.3569 0.01251 0.00695 -0.0459 0.1839 1.0000
9.500 1.3661 0.01314 0.00746 -0.0428 0.1640 1.0000
9.750 1.3753 0.01370 0.00794 -0.0397 0.1514 1.0000
10.000 1.3840 0.01420 0.00841 -0.0365 0.1431 1.0000
10.250 1.3913 0.01467 0.00886 -0.0330 0.1370 1.0000
10.500 1.3953 0.01515 0.00933 -0.0290 0.1320 1.0000
10.750 1.3953 0.01545 0.00966 -0.0240 0.1301 1.0000
11.000 1.3973 0.01584 0.01008 -0.0197 0.1281 1.0000
11.250 1.4018 0.01636 0.01061 -0.0161 0.1259 1.0000
11.500 1.4075 0.01701 0.01128 -0.0131 0.1236 1.0000
11.750 1.4135 0.01782 0.01211 -0.0106 0.1208 1.0000
12.000 1.4225 0.01863 0.01296 -0.0087 0.1187 1.0000
12.250 1.4353 0.01934 0.01372 -0.0074 0.1171 1.0000
12.500 1.4465 0.02023 0.01464 -0.0061 0.1150 1.0000
12.750 1.4569 0.02123 0.01568 -0.0049 0.1132 1.0000
13.000 1.4659 0.02240 0.01687 -0.0038 0.1111 1.0000
13.250 1.4743 0.02366 0.01817 -0.0027 0.1093 1.0000
13.500 1.4799 0.02518 0.01972 -0.0016 0.1069 1.0000
13.750 1.4940 0.02607 0.02067 -0.0010 0.1060 1.0000
14.000 1.5062 0.02712 0.02178 -0.0003 0.1042 1.0000
14.250 1.5158 0.02839 0.02309 0.0004 0.1020 1.0000
14.500 1.5228 0.02990 0.02462 0.0011 0.0994 1.0000
14.750 1.5266 0.03171 0.02646 0.0019 0.0965 1.0000
15.000 1.5352 0.03314 0.02794 0.0025 0.0945 1.0000
15.250 1.5447 0.03450 0.02936 0.0030 0.0918 1.0000
15.500 1.5494 0.03631 0.03118 0.0035 0.0877 1.0000
15.750 1.5519 0.03835 0.03324 0.0040 0.0835 1.0000
16.000 1.5514 0.04075 0.03562 0.0044 0.0759 1.0000
16.250 1.5427 0.04405 0.03887 0.0048 0.0652 1.0000
16.500 1.5252 0.04841 0.04319 0.0049 0.0544 1.0000
16.750 1.5117 0.05254 0.04733 0.0048 0.0478 1.0000
17.000 1.4954 0.05711 0.05191 0.0044 0.0410 1.0000
17.250 1.4777 0.06200 0.05682 0.0039 0.0341 1.0000
17.500 1.4581 0.06725 0.06209 0.0030 0.0271 1.0000
17.750 1.4455 0.07182 0.06670 0.0022 0.0240 1.0000
18.000 1.4301 0.07686 0.07179 0.0011 0.0211 1.0000
18.250 1.4180 0.08156 0.07656 0.0000 0.0196 1.0000
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Polar data table (+)
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