GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.17 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610b-il-1000000.txt Download as CSV file: xf-goe610b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2385 0.10705 0.10552 -0.0355 1.0000 0.0128
-10.500 -0.2354 0.10439 0.10288 -0.0355 1.0000 0.0130
-10.250 -0.3219 0.11028 0.10864 -0.0317 1.0000 0.0127
-10.000 -0.3162 0.10803 0.10640 -0.0319 1.0000 0.0129
-9.750 -0.3123 0.10539 0.10377 -0.0323 1.0000 0.0130
-9.500 -0.3079 0.10308 0.10148 -0.0325 1.0000 0.0132
-9.250 -0.3042 0.10076 0.09918 -0.0326 1.0000 0.0136
-8.250 -0.2496 0.08394 0.08237 -0.0514 0.9707 0.0158
-8.000 -0.2234 0.07821 0.07661 -0.0605 0.9570 0.0158
-7.750 -0.1911 0.07341 0.07177 -0.0687 0.9451 0.0166
-7.500 -0.1556 0.06608 0.06429 -0.0825 0.9136 0.0151
-7.250 -0.1452 0.06175 0.05977 -0.0872 0.8762 0.0151
-7.000 -0.1430 0.05652 0.05440 -0.0908 0.8553 0.0153
-6.750 -0.1423 0.04836 0.04608 -0.0966 0.8418 0.0161
-6.500 -0.1222 0.04758 0.04524 -0.0971 0.8340 0.0166
-6.250 -0.1009 0.04731 0.04494 -0.0972 0.8268 0.0172
-6.000 -0.0851 0.04281 0.04030 -0.0998 0.8198 0.0178
-5.750 -0.1129 0.01485 0.01060 -0.1026 0.8126 0.0255
-5.500 -0.0837 0.01577 0.01158 -0.1026 0.8071 0.0258
-5.250 -0.0547 0.01661 0.01253 -0.1027 0.8014 0.0261
-5.000 -0.0264 0.01739 0.01336 -0.1026 0.7954 0.0264
-4.750 0.0008 0.01776 0.01373 -0.1025 0.7896 0.0270
-4.500 0.0277 0.01800 0.01397 -0.1023 0.7830 0.0280
-4.250 0.0450 0.01404 0.00930 -0.1006 0.7770 0.0314
-4.000 0.0712 0.01387 0.00913 -0.1004 0.7698 0.0322
-3.750 0.0979 0.01409 0.00935 -0.1002 0.7622 0.0329
-3.500 0.1245 0.01408 0.00935 -0.1000 0.7533 0.0339
-3.250 0.1495 0.01338 0.00848 -0.0993 0.7428 0.0351
-3.000 0.1744 0.01274 0.00764 -0.0986 0.7266 0.0364
-2.750 0.1996 0.01259 0.00729 -0.0979 0.7027 0.0375
-2.250 0.2464 0.01097 0.00516 -0.0961 0.6500 0.0397
-1.500 0.3228 0.01026 0.00417 -0.0946 0.6043 0.0422
-1.250 0.3489 0.00996 0.00378 -0.0941 0.5953 0.0429
-1.000 0.3749 0.00966 0.00340 -0.0937 0.5867 0.0434
-0.750 0.4013 0.00943 0.00311 -0.0933 0.5798 0.0444
-0.500 0.4278 0.00930 0.00293 -0.0929 0.5732 0.0454
-0.250 0.4542 0.00919 0.00278 -0.0926 0.5667 0.0462
0.000 0.4809 0.00913 0.00268 -0.0922 0.5599 0.0468
0.250 0.5073 0.00910 0.00261 -0.0919 0.5540 0.0472
0.500 0.5329 0.00865 0.00215 -0.0914 0.5491 0.0480
0.750 0.5584 0.00843 0.00191 -0.0909 0.5436 0.0487
1.000 0.5842 0.00829 0.00175 -0.0904 0.5389 0.0497
1.250 0.6107 0.00817 0.00165 -0.0901 0.5344 0.0512
1.500 0.6370 0.00811 0.00160 -0.0897 0.5296 0.0530
2.000 0.6899 0.00805 0.00153 -0.0891 0.5196 0.0557
2.250 0.7163 0.00805 0.00152 -0.0887 0.5140 0.0566
2.500 0.7425 0.00807 0.00153 -0.0884 0.5081 0.0573
2.750 0.7692 0.00806 0.00154 -0.0881 0.5013 0.0580
3.000 0.7951 0.00810 0.00156 -0.0877 0.4939 0.0603
3.250 0.8217 0.00810 0.00159 -0.0874 0.4859 0.0663
3.500 0.8473 0.00810 0.00169 -0.0869 0.4765 0.1156
3.750 0.8568 0.00684 0.00192 -0.0835 0.4665 0.8110
4.000 0.9516 0.00720 0.00224 -0.0992 0.3805 1.0000
4.250 0.9675 0.00791 0.00261 -0.0970 0.3188 1.0000
4.500 0.9891 0.00822 0.00282 -0.0958 0.2982 1.0000
4.750 1.0117 0.00845 0.00301 -0.0948 0.2856 1.0000
5.000 1.0340 0.00871 0.00320 -0.0937 0.2704 1.0000
5.250 1.0561 0.00898 0.00340 -0.0927 0.2538 1.0000
5.500 1.0778 0.00926 0.00360 -0.0915 0.2361 1.0000
5.750 1.0991 0.00957 0.00382 -0.0903 0.2178 1.0000
6.000 1.1186 0.00998 0.00409 -0.0889 0.1876 1.0000
6.250 1.1316 0.01082 0.00461 -0.0863 0.1289 1.0000
6.500 1.1514 0.01121 0.00495 -0.0848 0.1180 1.0000
6.750 1.1715 0.01157 0.00528 -0.0835 0.1108 1.0000
7.000 1.1931 0.01182 0.00555 -0.0824 0.1058 1.0000
7.250 1.2141 0.01210 0.00584 -0.0812 0.0999 1.0000
7.500 1.2346 0.01241 0.00615 -0.0799 0.0922 1.0000
7.750 1.2490 0.01309 0.00659 -0.0776 0.0558 1.0000
8.000 1.2592 0.01401 0.00732 -0.0747 0.0271 1.0000
8.250 1.2749 0.01457 0.00786 -0.0726 0.0206 1.0000
8.500 1.2903 0.01512 0.00842 -0.0704 0.0178 1.0000
8.750 1.3055 0.01566 0.00901 -0.0683 0.0162 1.0000
9.000 1.3198 0.01612 0.00951 -0.0659 0.0153 1.0000
9.250 1.3325 0.01660 0.01003 -0.0633 0.0144 1.0000
9.500 1.3442 0.01716 0.01063 -0.0606 0.0136 1.0000
9.750 1.3498 0.01810 0.01165 -0.0571 0.0124 1.0000
10.000 1.3614 0.01876 0.01238 -0.0547 0.0120 1.0000
10.250 1.3754 0.01932 0.01298 -0.0528 0.0115 1.0000
10.500 1.3863 0.02009 0.01381 -0.0505 0.0111 1.0000
10.750 1.3973 0.02088 0.01466 -0.0484 0.0106 1.0000
11.000 1.4082 0.02172 0.01555 -0.0464 0.0102 1.0000
11.250 1.4175 0.02271 0.01660 -0.0444 0.0099 1.0000
11.500 1.4238 0.02397 0.01793 -0.0422 0.0096 1.0000
11.750 1.4195 0.02611 0.02019 -0.0393 0.0090 1.0000
12.000 1.4197 0.02803 0.02222 -0.0371 0.0088 1.0000
12.250 1.4283 0.02935 0.02361 -0.0357 0.0087 1.0000
12.500 1.4363 0.03074 0.02508 -0.0344 0.0085 1.0000
12.750 1.4418 0.03240 0.02682 -0.0330 0.0083 1.0000
13.000 1.4464 0.03419 0.02869 -0.0318 0.0081 1.0000
13.250 1.4528 0.03584 0.03042 -0.0307 0.0078 1.0000
13.500 1.4588 0.03758 0.03224 -0.0298 0.0077 1.0000
13.750 1.4604 0.03980 0.03454 -0.0288 0.0075 1.0000
14.000 1.4645 0.04184 0.03665 -0.0281 0.0073 1.0000
14.250 1.4659 0.04420 0.03910 -0.0274 0.0071 1.0000
14.500 1.4661 0.04678 0.04175 -0.0268 0.0070 1.0000
14.750 1.4659 0.04948 0.04453 -0.0264 0.0068 1.0000
15.000 1.4605 0.05284 0.04797 -0.0260 0.0066 1.0000
15.250 1.4497 0.05689 0.05215 -0.0256 0.0065 1.0000
15.500 1.4355 0.06137 0.05677 -0.0251 0.0063 1.0000
15.750 1.4285 0.06515 0.06068 -0.0250 0.0063 1.0000
16.000 1.4263 0.06855 0.06418 -0.0253 0.0062 1.0000
16.250 1.4244 0.07198 0.06772 -0.0258 0.0062 1.0000
16.500 1.4210 0.07567 0.07152 -0.0265 0.0061 1.0000
16.750 1.4155 0.07969 0.07566 -0.0272 0.0061 1.0000
17.000 1.4110 0.08378 0.07986 -0.0282 0.0060 1.0000
17.250 1.4026 0.08836 0.08457 -0.0292 0.0060 1.0000
17.500 1.3936 0.09316 0.08949 -0.0305 0.0060 1.0000
17.750 1.3863 0.09801 0.09446 -0.0322 0.0058 1.0000
18.000 1.3775 0.10315 0.09971 -0.0340 0.0058 1.0000
18.250 1.3643 0.10911 0.10582 -0.0362 0.0058 1.0000
18.500 1.3553 0.11465 0.11147 -0.0386 0.0057 1.0000
18.750 1.3438 0.12079 0.11774 -0.0414 0.0057 1.0000
19.000 1.3315 0.12721 0.12430 -0.0445 0.0057 1.0000
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