WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 100,000 Max Cl/Cd: 29.33 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617ai-il-100000-n5.txt Download as CSV file: xf-fx6617ai-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4007 0.08996 0.08463 -0.0627 0.7461 0.0313
-11.750 -0.4470 0.07670 0.07120 -0.0724 0.7438 0.0305
-11.500 -0.4815 0.06831 0.06254 -0.0784 0.7374 0.0300
-11.250 -0.5067 0.06227 0.05622 -0.0822 0.7296 0.0298
-11.000 -0.5249 0.05757 0.05122 -0.0847 0.7215 0.0297
-10.750 -0.5372 0.05367 0.04703 -0.0862 0.7135 0.0298
-10.500 -0.5450 0.05043 0.04348 -0.0870 0.7061 0.0299
-10.250 -0.5477 0.04793 0.04069 -0.0867 0.6991 0.0302
-10.000 -0.5438 0.04561 0.03807 -0.0865 0.6924 0.0309
-9.750 -0.5369 0.04337 0.03548 -0.0862 0.6866 0.0318
-9.500 -0.5267 0.04116 0.03290 -0.0858 0.6805 0.0326
-9.250 -0.5130 0.03904 0.03039 -0.0854 0.6753 0.0332
-9.000 -0.4956 0.03707 0.02806 -0.0850 0.6707 0.0337
-8.750 -0.4757 0.03533 0.02601 -0.0847 0.6655 0.0342
-8.500 -0.4541 0.03372 0.02417 -0.0844 0.6607 0.0348
-8.250 -0.4317 0.03221 0.02257 -0.0841 0.6567 0.0357
-8.000 -0.4092 0.03100 0.02129 -0.0838 0.6519 0.0366
-7.750 -0.3869 0.02995 0.02016 -0.0834 0.6473 0.0379
-7.500 -0.3646 0.02905 0.01913 -0.0831 0.6434 0.0400
-7.250 -0.3419 0.02823 0.01813 -0.0826 0.6401 0.0421
-7.000 -0.3208 0.02726 0.01717 -0.0821 0.6362 0.0439
-6.750 -0.3002 0.02640 0.01629 -0.0817 0.6326 0.0459
-6.500 -0.2790 0.02565 0.01547 -0.0812 0.6292 0.0484
-6.250 -0.2570 0.02501 0.01466 -0.0808 0.6262 0.0521
-6.000 -0.2361 0.02424 0.01389 -0.0806 0.6231 0.0573
-5.750 -0.2136 0.02361 0.01319 -0.0803 0.6193 0.0645
-5.500 -0.1916 0.02289 0.01248 -0.0801 0.6159 0.0769
-5.250 -0.1707 0.02193 0.01174 -0.0800 0.6130 0.1134
-5.000 -0.1527 0.02050 0.01091 -0.0800 0.6106 0.2299
-4.750 -0.1342 0.01950 0.01068 -0.0795 0.6084 0.3860
-4.500 -0.1100 0.01957 0.01099 -0.0789 0.6053 0.4651
-4.250 -0.0844 0.01993 0.01140 -0.0782 0.6022 0.5133
-4.000 -0.0583 0.02048 0.01186 -0.0775 0.5992 0.5507
-3.750 -0.0321 0.02107 0.01238 -0.0765 0.5965 0.5730
-3.500 -0.0052 0.02141 0.01256 -0.0760 0.5942 0.5877
-3.250 0.0220 0.02153 0.01249 -0.0760 0.5918 0.5986
-3.000 0.0484 0.02171 0.01262 -0.0758 0.5889 0.6050
-2.750 0.0755 0.02177 0.01254 -0.0761 0.5862 0.6141
-2.500 0.1019 0.02197 0.01268 -0.0757 0.5838 0.6208
-2.250 0.1293 0.02204 0.01259 -0.0759 0.5814 0.6301
-2.000 0.1564 0.02214 0.01260 -0.0757 0.5793 0.6351
-1.750 0.1846 0.02217 0.01246 -0.0761 0.5774 0.6411
-1.500 0.2111 0.02226 0.01249 -0.0764 0.5746 0.6468
-1.250 0.2371 0.02240 0.01263 -0.0763 0.5719 0.6509
-1.000 0.2639 0.02252 0.01269 -0.0765 0.5695 0.6562
-0.750 0.2915 0.02261 0.01268 -0.0770 0.5673 0.6620
-0.500 0.3183 0.02272 0.01274 -0.0770 0.5653 0.6657
-0.250 0.3460 0.02281 0.01275 -0.0773 0.5635 0.6705
0.000 0.3748 0.02288 0.01268 -0.0779 0.5618 0.6766
0.250 0.3996 0.02313 0.01297 -0.0778 0.5591 0.6803
0.500 0.4244 0.02340 0.01329 -0.0777 0.5563 0.6847
0.750 0.4505 0.02365 0.01353 -0.0780 0.5539 0.6901
1.000 0.4769 0.02387 0.01374 -0.0782 0.5518 0.6949
1.250 0.5032 0.02407 0.01393 -0.0782 0.5499 0.6991
1.500 0.5307 0.02423 0.01405 -0.0786 0.5482 0.7041
1.750 0.5592 0.02437 0.01413 -0.0790 0.5466 0.7095
2.000 0.5840 0.02467 0.01447 -0.0789 0.5444 0.7137
2.250 0.6057 0.02522 0.01513 -0.0787 0.5413 0.7187
2.500 0.6299 0.02570 0.01565 -0.0789 0.5387 0.7243
2.750 0.6537 0.02608 0.01610 -0.0787 0.5365 0.7285
3.000 0.6791 0.02638 0.01643 -0.0788 0.5345 0.7337
3.250 0.7064 0.02662 0.01666 -0.0791 0.5328 0.7394
3.500 0.7335 0.02678 0.01684 -0.0792 0.5312 0.7441
3.750 0.7590 0.02712 0.01721 -0.0793 0.5295 0.7495
4.000 0.7732 0.02830 0.01859 -0.0786 0.5256 0.7555
4.250 0.7916 0.02908 0.01950 -0.0780 0.5226 0.7605
4.500 0.8143 0.02961 0.02009 -0.0779 0.5201 0.7665
4.750 0.8397 0.02995 0.02048 -0.0780 0.5182 0.7726
5.000 0.8659 0.03019 0.02078 -0.0780 0.5166 0.7786
5.250 0.8934 0.03046 0.02107 -0.0784 0.5153 0.7857
5.500 0.8892 0.03286 0.02376 -0.0760 0.5095 0.7919
5.750 0.9021 0.03405 0.02509 -0.0752 0.5057 0.7996
6.000 0.9228 0.03461 0.02575 -0.0747 0.5034 0.8071
6.250 0.9468 0.03502 0.02624 -0.0747 0.5018 0.8158
6.500 0.9729 0.03520 0.02651 -0.0746 0.5005 0.8246
7.000 0.9392 0.04155 0.03328 -0.0688 0.4869 0.8508
7.250 0.9647 0.04154 0.03341 -0.0684 0.4857 0.8701
7.500 0.9938 0.04132 0.03334 -0.0683 0.4847 0.9067
8.500 0.8933 0.06274 0.05502 -0.0660 0.4439 1.0002
9.000 0.8994 0.06796 0.06034 -0.0657 0.4323 1.0002
9.250 0.9169 0.06910 0.06155 -0.0656 0.4294 1.0002
9.500 0.9400 0.06962 0.06214 -0.0656 0.4276 1.0002
9.750 0.9657 0.06982 0.06242 -0.0655 0.4263 1.0002
10.250 0.9641 0.07578 0.06852 -0.0651 0.4131 1.0002
10.500 0.9894 0.07595 0.06881 -0.0649 0.4117 1.0002
12.000 1.0077 0.09107 0.08450 -0.0639 0.3729 1.0002
12.250 1.0433 0.08901 0.08257 -0.0631 0.3699 1.0002
12.750 1.0657 0.09035 0.08411 -0.0620 0.3500 1.0002
13.000 1.1122 0.08542 0.07932 -0.0607 0.3396 1.0002
13.250 1.1131 0.08771 0.08170 -0.0606 0.3244 1.0002
13.500 1.1129 0.09050 0.08457 -0.0607 0.3083 1.0002
13.750 1.1169 0.09285 0.08703 -0.0607 0.2920 1.0002
14.000 1.1291 0.09402 0.08826 -0.0605 0.2721 1.0002
14.250 1.1698 0.08992 0.08352 -0.0587 0.1912 1.0002
14.750 1.1375 0.09986 0.09265 -0.0591 0.1092 1.0002
15.000 1.1248 0.10479 0.09738 -0.0596 0.0873 1.0002
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