RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Reynolds number: 500,000 Max Cl/Cd: 107.57 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1082t-il-500000.txt Download as CSV file: xf-r1082t-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4042 0.05251 0.04916 -0.1129 0.8394 0.0305
-10.250 -0.4283 0.05083 0.04717 -0.1088 0.8093 0.0306
-9.000 -0.5070 0.02883 0.02320 -0.0867 0.7458 0.0200
-8.750 -0.4974 0.02615 0.02019 -0.0844 0.7376 0.0192
-8.500 -0.4850 0.02253 0.01594 -0.0820 0.7303 0.0175
-8.250 -0.4642 0.02128 0.01444 -0.0809 0.7232 0.0173
-8.000 -0.4417 0.02003 0.01305 -0.0803 0.7170 0.0175
-7.750 -0.4190 0.01905 0.01196 -0.0797 0.7108 0.0176
-7.500 -0.3966 0.01823 0.01104 -0.0790 0.7054 0.0180
-7.250 -0.3741 0.01751 0.01026 -0.0783 0.7003 0.0184
-7.000 -0.3519 0.01680 0.00948 -0.0775 0.6952 0.0186
-6.750 -0.3301 0.01622 0.00882 -0.0766 0.6908 0.0192
-6.500 -0.3085 0.01568 0.00820 -0.0756 0.6866 0.0195
-6.250 -0.2870 0.01515 0.00762 -0.0747 0.6825 0.0200
-6.000 -0.2653 0.01471 0.00712 -0.0737 0.6784 0.0204
-5.750 -0.2454 0.01414 0.00649 -0.0725 0.6747 0.0213
-5.500 -0.2239 0.01373 0.00604 -0.0716 0.6712 0.0225
-5.250 -0.2012 0.01336 0.00566 -0.0708 0.6679 0.0237
-5.000 -0.1781 0.01304 0.00529 -0.0700 0.6646 0.0249
-4.750 -0.1557 0.01263 0.00486 -0.0691 0.6616 0.0277
-4.500 -0.1320 0.01235 0.00454 -0.0685 0.6589 0.0321
-4.250 -0.1117 0.01179 0.00417 -0.0674 0.6562 0.0714
-4.000 -0.0909 0.01128 0.00395 -0.0664 0.6538 0.1315
-3.750 -0.0694 0.01083 0.00375 -0.0656 0.6512 0.1919
-3.500 -0.0489 0.01030 0.00354 -0.0647 0.6487 0.2755
-3.250 -0.0315 0.00956 0.00330 -0.0633 0.6463 0.4048
-3.000 -0.0158 0.00874 0.00307 -0.0614 0.6439 0.5586
-2.750 0.0037 0.00844 0.00325 -0.0597 0.6417 0.6947
-2.500 0.0306 0.00863 0.00344 -0.0593 0.6395 0.7334
-2.250 0.0575 0.00880 0.00359 -0.0589 0.6376 0.7561
-2.000 0.0848 0.00897 0.00375 -0.0586 0.6356 0.7688
-1.750 0.1124 0.00911 0.00387 -0.0585 0.6335 0.7782
-1.500 0.1402 0.00924 0.00396 -0.0584 0.6316 0.7866
-1.250 0.1680 0.00936 0.00405 -0.0583 0.6297 0.7932
-1.000 0.1958 0.00952 0.00417 -0.0582 0.6279 0.8001
-0.750 0.2234 0.00968 0.00428 -0.0580 0.6260 0.8081
-0.500 0.2507 0.00996 0.00455 -0.0576 0.6240 0.8161
-0.250 0.2773 0.01007 0.00466 -0.0573 0.6226 0.8235
0.000 0.3039 0.01019 0.00481 -0.0569 0.6209 0.8282
0.250 0.3314 0.01027 0.00488 -0.0569 0.6192 0.8325
0.500 0.3594 0.01032 0.00491 -0.0571 0.6173 0.8365
0.750 0.3872 0.01034 0.00491 -0.0573 0.6153 0.8394
1.000 0.4149 0.01038 0.00495 -0.0573 0.6136 0.8417
1.250 0.4430 0.01044 0.00499 -0.0575 0.6120 0.8440
1.500 0.4715 0.01051 0.00504 -0.0578 0.6103 0.8465
1.750 0.5004 0.01065 0.00514 -0.0583 0.6083 0.8491
2.000 0.5280 0.01068 0.00519 -0.0585 0.6066 0.8516
2.250 0.5560 0.01070 0.00523 -0.0588 0.6046 0.8538
2.500 0.5830 0.01069 0.00525 -0.0588 0.6023 0.8555
2.750 0.6104 0.01071 0.00529 -0.0589 0.5999 0.8572
3.000 0.6383 0.01074 0.00532 -0.0591 0.5976 0.8589
3.250 0.6669 0.01077 0.00535 -0.0595 0.5953 0.8605
3.500 0.6960 0.01090 0.00544 -0.0599 0.5928 0.8623
3.750 0.7224 0.01091 0.00552 -0.0599 0.5901 0.8644
4.000 0.7493 0.01091 0.00557 -0.0600 0.5871 0.8663
4.250 0.7771 0.01091 0.00558 -0.0602 0.5836 0.8680
4.500 0.8058 0.01091 0.00557 -0.0607 0.5803 0.8696
4.750 0.8343 0.01097 0.00562 -0.0610 0.5768 0.8712
5.000 0.8584 0.01091 0.00566 -0.0604 0.5728 0.8731
5.250 0.8843 0.01086 0.00566 -0.0602 0.5682 0.8748
5.500 0.9115 0.01082 0.00563 -0.0602 0.5637 0.8766
5.750 0.9377 0.01084 0.00568 -0.0601 0.5589 0.8785
6.000 0.9624 0.01079 0.00570 -0.0597 0.5535 0.8807
6.250 0.9888 0.01075 0.00568 -0.0596 0.5481 0.8829
6.500 1.0143 0.01076 0.00574 -0.0594 0.5425 0.8851
6.750 1.0373 0.01069 0.00576 -0.0586 0.5357 0.8873
7.000 1.0614 0.01067 0.00577 -0.0580 0.5289 0.8895
7.250 1.0832 0.01062 0.00582 -0.0569 0.5197 0.8920
7.500 1.1056 0.01062 0.00588 -0.0561 0.5099 0.8948
7.750 1.1272 0.01064 0.00594 -0.0551 0.4980 0.8978
8.000 1.1477 0.01070 0.00604 -0.0539 0.4820 0.9008
8.250 1.1628 0.01081 0.00614 -0.0516 0.4581 0.9044
8.500 1.1704 0.01114 0.00636 -0.0480 0.4243 0.9095
8.750 1.1688 0.01169 0.00675 -0.0427 0.3878 0.9161
9.000 1.1639 0.01237 0.00732 -0.0370 0.3547 0.9239
9.250 1.1593 0.01316 0.00800 -0.0317 0.3232 0.9342
9.500 1.1530 0.01409 0.00884 -0.0265 0.2919 0.9509
9.750 1.1614 0.01551 0.01012 -0.0255 0.2510 0.9799
10.000 1.1617 0.01699 0.01144 -0.0232 0.2203 1.0000
10.250 1.1598 0.01863 0.01293 -0.0206 0.1928 1.0000
10.500 1.1596 0.02028 0.01447 -0.0184 0.1716 1.0000
10.750 1.1598 0.02199 0.01608 -0.0164 0.1501 1.0000
11.000 1.1605 0.02374 0.01775 -0.0146 0.1325 1.0000
11.250 1.1629 0.02544 0.01939 -0.0130 0.1179 1.0000
11.500 1.1666 0.02710 0.02100 -0.0116 0.1055 1.0000
11.750 1.1708 0.02876 0.02263 -0.0103 0.0944 1.0000
12.000 1.1754 0.03041 0.02426 -0.0092 0.0850 1.0000
12.250 1.1794 0.03214 0.02596 -0.0080 0.0769 1.0000
12.500 1.1844 0.03383 0.02765 -0.0070 0.0692 1.0000
12.750 1.1904 0.03548 0.02930 -0.0062 0.0627 1.0000
13.000 1.1942 0.03735 0.03115 -0.0053 0.0568 1.0000
13.250 1.2022 0.03892 0.03276 -0.0046 0.0521 1.0000
13.500 1.2054 0.04092 0.03474 -0.0039 0.0470 1.0000
13.750 1.2135 0.04254 0.03641 -0.0034 0.0431 1.0000
14.000 1.2168 0.04463 0.03850 -0.0027 0.0387 1.0000
14.250 1.2235 0.04645 0.04035 -0.0023 0.0345 1.0000
14.500 1.2271 0.04861 0.04253 -0.0019 0.0303 1.0000
14.750 1.2281 0.05107 0.04498 -0.0014 0.0265 1.0000
15.000 1.2323 0.05327 0.04723 -0.0011 0.0233 1.0000
15.250 1.2315 0.05605 0.05003 -0.0008 0.0209 1.0000
15.500 1.2361 0.05831 0.05236 -0.0007 0.0192 1.0000
15.750 1.2362 0.06111 0.05520 -0.0006 0.0179 1.0000
16.000 1.2346 0.06418 0.05833 -0.0007 0.0170 1.0000
16.250 1.2389 0.06665 0.06089 -0.0008 0.0162 1.0000
16.500 1.2415 0.06936 0.06369 -0.0011 0.0155 1.0000
16.750 1.2424 0.07231 0.06671 -0.0015 0.0150 1.0000
17.000 1.2411 0.07563 0.07008 -0.0020 0.0144 1.0000
17.250 1.2351 0.07960 0.07413 -0.0026 0.0139 1.0000
17.500 1.2329 0.08316 0.07777 -0.0033 0.0137 1.0000
17.750 1.2337 0.08641 0.08114 -0.0041 0.0134 1.0000
18.000 1.2334 0.08986 0.08468 -0.0050 0.0131 1.0000
18.250 1.2330 0.09335 0.08827 -0.0060 0.0129 1.0000
18.500 1.2318 0.09705 0.09207 -0.0072 0.0126 1.0000
18.750 1.2307 0.10078 0.09589 -0.0084 0.0123 1.0000
19.000 1.2288 0.10466 0.09986 -0.0098 0.0120 1.0000
19.250 1.2275 0.10846 0.10374 -0.0113 0.0119 1.0000
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