GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.56 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe623-il-1000000.txt Download as CSV file: xf-goe623-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9407 0.03984 0.03728 -0.0791 1.0000 0.0131
-13.500 -0.9589 0.03511 0.03234 -0.0819 1.0000 0.0132
-13.250 -0.9611 0.03287 0.02994 -0.0808 1.0000 0.0133
-13.000 -0.9746 0.02919 0.02597 -0.0790 1.0000 0.0135
-12.750 -0.9688 0.02757 0.02424 -0.0771 1.0000 0.0138
-12.500 -0.9554 0.02677 0.02340 -0.0756 1.0000 0.0140
-12.250 -0.9406 0.02620 0.02280 -0.0739 1.0000 0.0142
-12.000 -0.9271 0.02567 0.02224 -0.0719 1.0000 0.0145
-11.750 -0.9052 0.02504 0.02155 -0.0717 0.9992 0.0148
-11.500 -0.8731 0.02414 0.02054 -0.0736 0.9970 0.0152
-11.250 -0.8414 0.02311 0.01938 -0.0754 0.9949 0.0157
-11.000 -0.8104 0.02217 0.01830 -0.0770 0.9922 0.0161
-10.750 -0.7784 0.02153 0.01754 -0.0785 0.9887 0.0164
-10.500 -0.7509 0.01977 0.01561 -0.0799 0.9849 0.0171
-10.250 -0.7200 0.01942 0.01526 -0.0809 0.9800 0.0175
-10.000 -0.6896 0.01912 0.01492 -0.0818 0.9737 0.0180
-9.750 -0.6609 0.01862 0.01435 -0.0823 0.9662 0.0185
-9.500 -0.6334 0.01804 0.01367 -0.0826 0.9572 0.0190
-9.250 -0.6081 0.01752 0.01303 -0.0823 0.9461 0.0196
-9.000 -0.5825 0.01715 0.01254 -0.0819 0.9355 0.0200
-8.750 -0.5603 0.01603 0.01124 -0.0812 0.9248 0.0206
-8.500 -0.5361 0.01542 0.01058 -0.0807 0.9148 0.0212
-8.250 -0.5101 0.01514 0.01025 -0.0805 0.9064 0.0218
-8.000 -0.4841 0.01482 0.00985 -0.0802 0.8983 0.0224
-7.750 -0.4579 0.01442 0.00937 -0.0799 0.8910 0.0230
-7.500 -0.4316 0.01402 0.00888 -0.0796 0.8834 0.0237
-7.250 -0.4048 0.01374 0.00850 -0.0794 0.8765 0.0242
-7.000 -0.3776 0.01349 0.00816 -0.0792 0.8692 0.0247
-6.750 -0.3538 0.01236 0.00695 -0.0787 0.8627 0.0257
-6.500 -0.3270 0.01194 0.00651 -0.0786 0.8561 0.0264
-6.250 -0.3001 0.01160 0.00611 -0.0784 0.8495 0.0271
-6.000 -0.2728 0.01128 0.00574 -0.0782 0.8429 0.0279
-5.750 -0.2454 0.01100 0.00541 -0.0781 0.8357 0.0287
-5.500 -0.2179 0.01074 0.00508 -0.0780 0.8290 0.0293
-5.250 -0.1900 0.01051 0.00480 -0.0779 0.8217 0.0297
-5.000 -0.1635 0.01000 0.00421 -0.0776 0.8147 0.0304
-4.750 -0.1363 0.00956 0.00373 -0.0775 0.8071 0.0316
-4.500 -0.1088 0.00932 0.00343 -0.0773 0.7992 0.0326
-4.250 -0.0807 0.00908 0.00316 -0.0773 0.7903 0.0335
-4.000 -0.0529 0.00889 0.00291 -0.0772 0.7813 0.0344
-3.750 -0.0248 0.00871 0.00269 -0.0772 0.7712 0.0353
-3.500 0.0034 0.00857 0.00250 -0.0771 0.7607 0.0360
-3.250 0.0312 0.00836 0.00223 -0.0770 0.7488 0.0383
-3.000 0.0591 0.00822 0.00204 -0.0769 0.7350 0.0406
-2.750 0.0871 0.00812 0.00188 -0.0768 0.7198 0.0434
-2.500 0.1145 0.00788 0.00172 -0.0767 0.7038 0.0690
-2.250 0.1417 0.00764 0.00163 -0.0767 0.6872 0.1220
-2.000 0.1696 0.00762 0.00159 -0.0766 0.6713 0.1410
-1.750 0.1975 0.00761 0.00155 -0.0766 0.6557 0.1537
-1.500 0.2255 0.00763 0.00151 -0.0765 0.6399 0.1617
-1.250 0.2534 0.00764 0.00147 -0.0765 0.6258 0.1705
-1.000 0.2815 0.00763 0.00144 -0.0765 0.6140 0.1813
-0.750 0.3096 0.00758 0.00142 -0.0766 0.6028 0.1991
-0.500 0.3372 0.00748 0.00140 -0.0766 0.5911 0.2423
-0.250 0.3646 0.00732 0.00141 -0.0766 0.5806 0.3161
0.000 0.3920 0.00702 0.00141 -0.0767 0.5726 0.4250
0.250 0.4182 0.00664 0.00145 -0.0766 0.5650 0.5758
0.500 0.4437 0.00622 0.00150 -0.0761 0.5584 0.7349
0.750 0.4667 0.00593 0.00158 -0.0748 0.5519 0.8622
1.000 0.4903 0.00586 0.00165 -0.0735 0.5459 0.9324
1.250 0.5240 0.00589 0.00169 -0.0746 0.5386 0.9739
1.500 0.5630 0.00598 0.00173 -0.0770 0.5307 0.9911
2.000 0.6354 0.00615 0.00180 -0.0807 0.5156 1.0000
2.250 0.6615 0.00621 0.00183 -0.0803 0.5083 1.0000
2.500 0.6872 0.00631 0.00188 -0.0798 0.5007 1.0000
2.750 0.7136 0.00638 0.00193 -0.0795 0.4924 1.0000
3.000 0.7397 0.00648 0.00199 -0.0791 0.4829 1.0000
3.250 0.7659 0.00660 0.00206 -0.0788 0.4714 1.0000
3.500 0.7925 0.00671 0.00213 -0.0786 0.4594 1.0000
3.750 0.8189 0.00684 0.00221 -0.0783 0.4456 1.0000
4.000 0.8451 0.00701 0.00231 -0.0780 0.4283 1.0000
4.250 0.8708 0.00723 0.00243 -0.0777 0.4067 1.0000
4.500 0.8959 0.00751 0.00259 -0.0772 0.3794 1.0000
4.750 0.9206 0.00783 0.00278 -0.0768 0.3515 1.0000
5.000 0.9454 0.00816 0.00298 -0.0763 0.3267 1.0000
5.250 0.9700 0.00850 0.00321 -0.0758 0.3042 1.0000
5.500 0.9950 0.00880 0.00343 -0.0755 0.2852 1.0000
5.750 1.0202 0.00909 0.00365 -0.0751 0.2687 1.0000
6.000 1.0453 0.00938 0.00387 -0.0747 0.2540 1.0000
6.250 1.0702 0.00969 0.00411 -0.0743 0.2396 1.0000
6.500 1.0949 0.01000 0.00436 -0.0739 0.2263 1.0000
7.000 1.1447 0.01057 0.00484 -0.0732 0.2042 1.0000
7.250 1.1693 0.01087 0.00510 -0.0728 0.1951 1.0000
7.500 1.1942 0.01113 0.00535 -0.0724 0.1883 1.0000
7.750 1.2186 0.01142 0.00562 -0.0720 0.1810 1.0000
8.000 1.2432 0.01169 0.00588 -0.0716 0.1744 1.0000
8.250 1.2671 0.01200 0.00617 -0.0711 0.1680 1.0000
8.500 1.2917 0.01225 0.00643 -0.0707 0.1623 1.0000
8.750 1.3146 0.01260 0.00675 -0.0700 0.1542 1.0000
9.000 1.3382 0.01290 0.00705 -0.0695 0.1466 1.0000
9.250 1.3607 0.01326 0.00739 -0.0688 0.1377 1.0000
9.500 1.3815 0.01372 0.00778 -0.0679 0.1239 1.0000
9.750 1.3936 0.01475 0.00855 -0.0657 0.0856 1.0000
10.000 1.3978 0.01622 0.00976 -0.0623 0.0486 1.0000
10.250 1.4077 0.01710 0.01057 -0.0596 0.0354 1.0000
10.500 1.4181 0.01796 0.01138 -0.0571 0.0258 1.0000
10.750 1.4304 0.01874 0.01215 -0.0550 0.0213 1.0000
11.000 1.4421 0.01960 0.01301 -0.0529 0.0187 1.0000
11.250 1.4561 0.02033 0.01380 -0.0512 0.0175 1.0000
11.500 1.4686 0.02117 0.01468 -0.0495 0.0164 1.0000
11.750 1.4786 0.02223 0.01578 -0.0476 0.0153 1.0000
12.000 1.4891 0.02329 0.01691 -0.0460 0.0146 1.0000
12.250 1.5012 0.02428 0.01795 -0.0446 0.0141 1.0000
12.500 1.5120 0.02538 0.01912 -0.0432 0.0135 1.0000
12.750 1.5211 0.02666 0.02046 -0.0418 0.0130 1.0000
13.000 1.5273 0.02823 0.02209 -0.0403 0.0125 1.0000
13.250 1.5279 0.03033 0.02429 -0.0386 0.0119 1.0000
13.500 1.5345 0.03200 0.02604 -0.0375 0.0117 1.0000
13.750 1.5412 0.03370 0.02781 -0.0365 0.0115 1.0000
14.000 1.5463 0.03560 0.02980 -0.0356 0.0112 1.0000
14.250 1.5502 0.03770 0.03198 -0.0348 0.0109 1.0000
14.500 1.5526 0.04001 0.03437 -0.0341 0.0107 1.0000
14.750 1.5537 0.04252 0.03697 -0.0336 0.0104 1.0000
15.000 1.5537 0.04527 0.03980 -0.0333 0.0102 1.0000
15.250 1.5518 0.04832 0.04294 -0.0331 0.0100 1.0000
15.500 1.5465 0.05188 0.04660 -0.0331 0.0098 1.0000
15.750 1.5378 0.05602 0.05084 -0.0334 0.0096 1.0000
16.000 1.5245 0.06086 0.05580 -0.0340 0.0094 1.0000
16.250 1.5068 0.06643 0.06151 -0.0348 0.0093 1.0000
16.500 1.5018 0.07042 0.06560 -0.0356 0.0092 1.0000
16.750 1.4971 0.07443 0.06970 -0.0364 0.0091 1.0000
17.000 1.4892 0.07894 0.07432 -0.0374 0.0090 1.0000
17.250 1.4801 0.08372 0.07921 -0.0386 0.0089 1.0000
17.500 1.4700 0.08877 0.08436 -0.0400 0.0088 1.0000
17.750 1.4581 0.09416 0.08987 -0.0416 0.0088 1.0000
18.000 1.4463 0.09961 0.09542 -0.0433 0.0087 1.0000
18.250 1.4346 0.10516 0.10108 -0.0451 0.0086 1.0000
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