RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.96 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1082t-il-1000000.txt Download as CSV file: xf-r1082t-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2376 0.08536 0.08309 -0.0860 0.8120 0.0172
-12.500 -0.2415 0.08106 0.07872 -0.0875 0.7951 0.0173
-12.250 -0.2462 0.07649 0.07411 -0.0891 0.7815 0.0175
-11.000 -0.6302 0.02718 0.02248 -0.0990 0.7769 0.0109
-10.750 -0.6287 0.02601 0.02111 -0.0955 0.7615 0.0109
-10.500 -0.6256 0.02482 0.01971 -0.0920 0.7486 0.0108
-10.000 -0.6035 0.02259 0.01711 -0.0876 0.7263 0.0107
-9.750 -0.5889 0.02157 0.01592 -0.0859 0.7170 0.0107
-9.500 -0.5730 0.02018 0.01439 -0.0845 0.7082 0.0109
-9.250 -0.5552 0.01933 0.01344 -0.0833 0.7006 0.0111
-9.000 -0.5365 0.01855 0.01256 -0.0821 0.6932 0.0113
-8.750 -0.5173 0.01785 0.01177 -0.0810 0.6867 0.0115
-8.500 -0.4970 0.01704 0.01087 -0.0800 0.6807 0.0115
-8.250 -0.4769 0.01635 0.01009 -0.0789 0.6749 0.0115
-8.000 -0.4564 0.01574 0.00940 -0.0778 0.6699 0.0118
-7.750 -0.4354 0.01518 0.00878 -0.0769 0.6650 0.0120
-7.500 -0.4144 0.01468 0.00821 -0.0759 0.6602 0.0123
-7.250 -0.3931 0.01425 0.00771 -0.0749 0.6557 0.0127
-7.000 -0.3715 0.01375 0.00716 -0.0740 0.6522 0.0128
-6.750 -0.3489 0.01339 0.00675 -0.0732 0.6482 0.0131
-6.500 -0.3265 0.01304 0.00634 -0.0724 0.6443 0.0133
-6.250 -0.3042 0.01271 0.00595 -0.0715 0.6404 0.0134
-6.000 -0.2844 0.01209 0.00527 -0.0703 0.6375 0.0139
-5.750 -0.2619 0.01167 0.00483 -0.0694 0.6346 0.0144
-5.500 -0.2382 0.01138 0.00452 -0.0688 0.6317 0.0149
-5.250 -0.2140 0.01113 0.00423 -0.0683 0.6288 0.0154
-5.000 -0.1896 0.01093 0.00398 -0.0678 0.6259 0.0162
-4.750 -0.1652 0.01068 0.00369 -0.0672 0.6233 0.0174
-4.500 -0.1403 0.01043 0.00344 -0.0668 0.6213 0.0189
-4.250 -0.1147 0.01023 0.00322 -0.0665 0.6191 0.0206
-4.000 -0.0907 0.00991 0.00298 -0.0659 0.6168 0.0337
-3.750 -0.0684 0.00947 0.00275 -0.0651 0.6146 0.0815
-3.500 -0.0443 0.00919 0.00260 -0.0647 0.6123 0.1193
-3.250 -0.0208 0.00888 0.00246 -0.0641 0.6098 0.1694
-3.000 0.0020 0.00848 0.00232 -0.0635 0.6077 0.2443
-2.750 0.0234 0.00791 0.00215 -0.0627 0.6062 0.3499
-2.500 0.0441 0.00729 0.00197 -0.0618 0.6045 0.4764
-2.250 0.0649 0.00667 0.00181 -0.0608 0.6028 0.6064
-2.000 0.0891 0.00644 0.00187 -0.0602 0.6011 0.6979
-1.750 0.1169 0.00648 0.00193 -0.0601 0.5995 0.7285
-1.500 0.1450 0.00655 0.00200 -0.0602 0.5978 0.7456
-1.250 0.1736 0.00664 0.00204 -0.0604 0.5961 0.7547
-1.000 0.2021 0.00671 0.00208 -0.0606 0.5941 0.7608
-0.750 0.2308 0.00682 0.00216 -0.0608 0.5921 0.7668
-0.500 0.2595 0.00688 0.00219 -0.0610 0.5909 0.7728
-0.250 0.2879 0.00691 0.00225 -0.0611 0.5896 0.7787
0.000 0.3163 0.00700 0.00235 -0.0613 0.5882 0.7857
0.250 0.3447 0.00707 0.00240 -0.0614 0.5868 0.7914
0.500 0.3730 0.00713 0.00248 -0.0615 0.5852 0.7961
0.750 0.4015 0.00719 0.00253 -0.0617 0.5835 0.7999
1.000 0.4302 0.00725 0.00257 -0.0620 0.5820 0.8030
1.250 0.4590 0.00732 0.00262 -0.0624 0.5804 0.8054
1.500 0.4876 0.00737 0.00264 -0.0627 0.5784 0.8077
1.750 0.5163 0.00744 0.00272 -0.0630 0.5763 0.8099
2.000 0.5445 0.00745 0.00275 -0.0632 0.5747 0.8119
2.250 0.5728 0.00746 0.00279 -0.0634 0.5727 0.8139
2.500 0.6012 0.00748 0.00282 -0.0637 0.5706 0.8157
2.750 0.6296 0.00750 0.00284 -0.0640 0.5683 0.8174
3.000 0.6579 0.00753 0.00286 -0.0642 0.5659 0.8189
3.250 0.6863 0.00760 0.00291 -0.0646 0.5632 0.8203
3.500 0.7148 0.00768 0.00298 -0.0649 0.5603 0.8215
3.750 0.7426 0.00765 0.00299 -0.0651 0.5578 0.8228
4.000 0.7702 0.00763 0.00301 -0.0652 0.5547 0.8243
4.250 0.7978 0.00763 0.00303 -0.0653 0.5513 0.8257
4.500 0.8251 0.00768 0.00307 -0.0654 0.5474 0.8272
4.750 0.8525 0.00772 0.00314 -0.0655 0.5437 0.8287
5.000 0.8798 0.00771 0.00318 -0.0655 0.5395 0.8302
5.250 0.9069 0.00772 0.00321 -0.0656 0.5350 0.8317
5.500 0.9335 0.00780 0.00328 -0.0656 0.5301 0.8332
5.750 0.9608 0.00779 0.00334 -0.0656 0.5253 0.8347
6.000 0.9876 0.00782 0.00339 -0.0656 0.5194 0.8362
6.250 1.0138 0.00789 0.00347 -0.0655 0.5129 0.8377
6.500 1.0397 0.00791 0.00352 -0.0653 0.5033 0.8396
6.750 1.0651 0.00796 0.00361 -0.0651 0.4928 0.8414
7.000 1.0891 0.00807 0.00371 -0.0646 0.4776 0.8432
7.250 1.1103 0.00828 0.00386 -0.0635 0.4545 0.8452
7.500 1.1246 0.00876 0.00416 -0.0612 0.4125 0.8475
7.750 1.1363 0.00935 0.00458 -0.0585 0.3722 0.8501
8.000 1.1439 0.01006 0.00508 -0.0551 0.3293 0.8528
8.250 1.1455 0.01074 0.00557 -0.0505 0.2902 0.8562
8.500 1.1499 0.01134 0.00606 -0.0465 0.2611 0.8599
8.750 1.1511 0.01208 0.00666 -0.0420 0.2298 0.8642
9.000 1.1538 0.01281 0.00727 -0.0381 0.2033 0.8684
9.250 1.1563 0.01355 0.00794 -0.0342 0.1808 0.8731
9.500 1.1568 0.01440 0.00872 -0.0303 0.1598 0.8788
9.750 1.1591 0.01531 0.00957 -0.0269 0.1424 0.8849
10.000 1.1608 0.01626 0.01051 -0.0236 0.1264 0.8925
10.250 1.1629 0.01731 0.01154 -0.0206 0.1122 0.9020
10.500 1.1647 0.01838 0.01263 -0.0177 0.0999 0.9166
10.750 1.1702 0.01948 0.01380 -0.0157 0.0888 0.9492
11.000 1.1911 0.02083 0.01514 -0.0173 0.0764 1.0000
11.250 1.1987 0.02210 0.01639 -0.0160 0.0691 1.0000
11.500 1.2071 0.02336 0.01764 -0.0148 0.0622 1.0000
11.750 1.2138 0.02475 0.01900 -0.0135 0.0559 1.0000
12.000 1.2219 0.02608 0.02034 -0.0124 0.0507 1.0000
12.250 1.2294 0.02747 0.02172 -0.0113 0.0461 1.0000
12.500 1.2373 0.02885 0.02311 -0.0103 0.0421 1.0000
12.750 1.2440 0.03034 0.02460 -0.0093 0.0380 1.0000
13.000 1.2518 0.03178 0.02606 -0.0084 0.0348 1.0000
13.250 1.2584 0.03335 0.02763 -0.0075 0.0311 1.0000
13.500 1.2647 0.03496 0.02924 -0.0066 0.0275 1.0000
13.750 1.2700 0.03670 0.03098 -0.0058 0.0231 1.0000
14.000 1.2752 0.03848 0.03277 -0.0050 0.0196 1.0000
14.250 1.2789 0.04044 0.03472 -0.0043 0.0161 1.0000
14.500 1.2819 0.04251 0.03680 -0.0036 0.0139 1.0000
14.750 1.2888 0.04427 0.03861 -0.0031 0.0127 1.0000
15.000 1.2937 0.04626 0.04063 -0.0026 0.0118 1.0000
15.250 1.2963 0.04850 0.04291 -0.0021 0.0108 1.0000
15.500 1.3028 0.05041 0.04490 -0.0018 0.0104 1.0000
15.750 1.3085 0.05244 0.04698 -0.0016 0.0100 1.0000
16.000 1.3130 0.05463 0.04923 -0.0014 0.0097 1.0000
16.250 1.3177 0.05683 0.05149 -0.0013 0.0094 1.0000
16.500 1.3201 0.05934 0.05404 -0.0013 0.0090 1.0000
16.750 1.3212 0.06202 0.05680 -0.0013 0.0088 1.0000
17.000 1.3183 0.06525 0.06012 -0.0014 0.0085 1.0000
17.250 1.3211 0.06790 0.06283 -0.0016 0.0083 1.0000
17.500 1.3239 0.07058 0.06560 -0.0020 0.0083 1.0000
17.750 1.3248 0.07355 0.06865 -0.0024 0.0081 1.0000
18.000 1.3255 0.07658 0.07177 -0.0029 0.0080 1.0000
18.250 1.3254 0.07981 0.07508 -0.0036 0.0079 1.0000
18.500 1.3251 0.08312 0.07847 -0.0044 0.0077 1.0000
18.750 1.3247 0.08650 0.08193 -0.0053 0.0076 1.0000
19.000 1.3208 0.09045 0.08597 -0.0064 0.0074 1.0000
19.250 1.3176 0.09436 0.08997 -0.0076 0.0074 1.0000
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