RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Reynolds number: 50,000 Max Cl/Cd: 4.25 at α=12° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1082-il-50000.txt Download as CSV file: xf-r1082-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2264 0.11664 0.11143 -0.0462 0.9476 0.3349
-8.750 -0.2536 0.11529 0.11015 -0.0456 0.9455 0.3466
-8.500 -0.4818 0.09374 0.08839 -0.0602 0.9602 0.1666
-8.250 -0.5327 0.08977 0.08438 -0.0580 0.9557 0.1531
-8.000 -0.6022 0.08619 0.08057 -0.0532 0.9520 0.1434
-7.750 -0.6096 0.08211 0.07642 -0.0518 0.9491 0.1368
-7.500 -0.6533 0.07797 0.07178 -0.0472 0.9479 0.1281
-7.250 -0.6559 0.07474 0.06845 -0.0450 0.9470 0.1252
-7.000 -0.6683 0.07162 0.06509 -0.0416 0.9473 0.1220
-6.750 -0.6871 0.06794 0.06088 -0.0373 0.9485 0.1178
-6.500 -0.6992 0.06528 0.05746 -0.0328 0.9502 0.1145
-6.250 -0.6964 0.06269 0.05459 -0.0303 0.9513 0.1142
-6.000 -0.6942 0.06035 0.05187 -0.0274 0.9541 0.1144
-5.750 -0.6880 0.05821 0.04931 -0.0249 0.9582 0.1148
-5.500 -0.7648 0.05771 0.04930 -0.0075 1.0000 0.1139
-5.250 -0.7524 0.05512 0.04623 -0.0059 1.0000 0.1144
-5.000 -0.7379 0.05275 0.04339 -0.0045 1.0000 0.1148
-4.750 -0.7217 0.05014 0.04053 -0.0034 1.0000 0.1162
-4.500 -0.7042 0.04817 0.03841 -0.0023 1.0000 0.1183
-4.250 -0.6863 0.04669 0.03676 -0.0013 1.0000 0.1229
-4.000 -0.6672 0.04535 0.03494 0.0000 1.0000 0.1293
-3.750 -0.6481 0.04389 0.03354 0.0009 1.0000 0.1370
-3.500 -0.6276 0.04271 0.03221 0.0020 1.0000 0.1482
-3.250 -0.6072 0.04171 0.03129 0.0031 1.0000 0.1657
-3.000 -0.5869 0.04080 0.03054 0.0044 1.0000 0.1965
-2.750 -0.5686 0.03977 0.02991 0.0060 1.0000 0.2467
-2.500 -0.5550 0.03805 0.02915 0.0081 1.0000 0.3432
-2.250 -0.5720 0.03766 0.03164 0.0224 1.0000 0.7617
-2.000 -0.2182 0.05405 0.04598 -0.0251 1.0000 1.0000
-1.750 -0.2148 0.05382 0.04557 -0.0232 1.0000 1.0000
-1.500 -0.2110 0.05368 0.04524 -0.0213 1.0000 1.0000
-1.250 -0.2066 0.05358 0.04496 -0.0194 1.0000 1.0000
-1.000 -0.2019 0.05352 0.04474 -0.0175 1.0000 1.0000
-0.750 -0.1970 0.05351 0.04457 -0.0156 1.0000 1.0000
-0.500 -0.1918 0.05353 0.04444 -0.0136 1.0000 1.0000
-0.250 -0.1865 0.05357 0.04432 -0.0117 1.0000 1.0000
0.000 -0.1811 0.05363 0.04425 -0.0098 1.0000 1.0000
0.250 -0.1756 0.05371 0.04421 -0.0079 1.0000 1.0000
0.500 -0.1701 0.05380 0.04418 -0.0059 1.0000 1.0000
0.750 -0.1645 0.05391 0.04417 -0.0040 1.0000 1.0000
1.000 -0.1590 0.05403 0.04418 -0.0020 1.0000 1.0000
1.250 -0.1536 0.05415 0.04420 -0.0001 1.0000 1.0000
1.500 -0.1482 0.05427 0.04423 0.0019 1.0000 1.0000
1.750 -0.1429 0.05440 0.04427 0.0038 1.0000 1.0000
2.000 -0.1338 0.05472 0.04449 0.0050 0.9988 1.0000
2.250 -0.1065 0.05620 0.04587 0.0024 0.9899 1.0000
2.500 -0.0820 0.05761 0.04718 0.0005 0.9800 1.0000
2.750 -0.0593 0.05894 0.04843 -0.0009 0.9692 1.0000
3.000 -0.0356 0.06063 0.05002 -0.0025 0.9584 1.0000
3.250 -0.0160 0.06160 0.05093 -0.0032 0.9458 1.0000
3.500 -0.0013 0.06222 0.05149 -0.0030 0.9329 1.0000
3.750 0.0124 0.06306 0.05228 -0.0026 0.9215 1.0000
4.000 0.0394 0.06569 0.05481 -0.0044 0.9124 1.0000
4.250 0.0489 0.06564 0.05473 -0.0032 0.8984 1.0000
4.500 0.0597 0.06631 0.05535 -0.0022 0.8869 1.0000
4.750 0.0912 0.06944 0.05842 -0.0048 0.8786 1.0000
5.000 0.0989 0.06933 0.05828 -0.0034 0.8647 1.0000
5.250 0.1110 0.07029 0.05921 -0.0028 0.8536 1.0000
5.500 0.1443 0.07349 0.06237 -0.0057 0.8450 1.0000
5.750 0.1514 0.07361 0.06249 -0.0044 0.8315 1.0000
6.000 0.1648 0.07493 0.06379 -0.0042 0.8210 1.0000
6.250 0.1972 0.07800 0.06684 -0.0069 0.8115 1.0000
6.500 0.2032 0.07837 0.06723 -0.0056 0.7984 1.0000
6.750 0.2195 0.08023 0.06909 -0.0060 0.7889 1.0000
7.000 0.2478 0.08287 0.07174 -0.0080 0.7777 1.0000
7.250 0.2536 0.08360 0.07249 -0.0070 0.7652 1.0000
7.500 0.2759 0.08628 0.07520 -0.0083 0.7567 1.0000
7.750 0.2961 0.08819 0.07715 -0.0092 0.7439 1.0000
8.000 0.3021 0.08930 0.07829 -0.0084 0.7317 1.0000
8.250 0.3298 0.09268 0.08170 -0.0105 0.7234 1.0000
8.500 0.3433 0.09411 0.08320 -0.0106 0.7098 1.0000
8.750 0.3488 0.09542 0.08456 -0.0100 0.6976 1.0000
9.000 0.3740 0.09875 0.08795 -0.0118 0.6890 1.0000
9.250 0.3912 0.10072 0.08998 -0.0124 0.6751 1.0000
9.500 0.3932 0.10197 0.09130 -0.0116 0.6629 1.0000
9.750 0.4104 0.10478 0.09417 -0.0126 0.6534 1.0000
10.000 0.4402 0.10816 0.09765 -0.0145 0.6403 1.0000
10.250 0.4368 0.10901 0.09855 -0.0135 0.6275 1.0000
10.500 0.4458 0.11131 0.10093 -0.0138 0.6165 1.0000
10.750 0.4751 0.11515 0.10488 -0.0157 0.6056 1.0000
11.000 0.4870 0.11708 0.10690 -0.0160 0.5911 1.0000
11.250 0.4846 0.11865 0.10853 -0.0156 0.5794 1.0000
11.500 0.4968 0.12148 0.11145 -0.0164 0.5691 1.0000
11.750 0.5225 0.12502 0.11511 -0.0178 0.5563 1.0000
12.000 0.5437 0.12794 0.11814 -0.0188 0.5411 1.0000
12.250 0.5310 0.12902 0.11928 -0.0182 0.5306 1.0000
12.500 0.5409 0.13201 0.12236 -0.0191 0.5208 1.0000
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